Airworthiness Directives; Pratt & Whitney PW4000 Series Turbofan Engines

[Federal Register Volume 68, Number 189 (Tuesday, September 30, 2003)]
[Rules and Regulations]
[Pages 56143-56152]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-24486]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-47-AD; Amendment 39-13318; AD 2003-19-15]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney PW4000 Series Turbofan 
Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), that is applicable to Pratt & Whitney (PW) models PW4050, PW4052, 
PW4056, PW4060, PW4060A, PW4060C, PW4062, PW4152, PW4156, PW4156A, 
PW4158, PW4160, PW4460, PW4462, and PW4650 turbofan engines. That AD 
currently requires interim actions to address engine takeoff power loss 
events until the high-pressure-compressor (HPC) case is redesigned and 
available for incorporation on the PW4000 engines. That amendment also 
requires terminating actions for engines installed in the Boeing fleet 
by incorporating a new Ring Case Configuration (RCC) rear HPC. This 
amendment requires the same interim and terminating action requirements 
as that AD, and in addition, expands the terminating action 
requirements to engines installed on Airbus and McDonnell Douglas 
fleets. This amendment is prompted by the certification of an RCC rear 
HPC for PW4000 series turbofan engines installed in the Airbus fleet 
and McDonnell Douglas fleet. The actions specified by this AD are 
intended to prevent engine takeoff power losses due to HPC surge.

DATES: Effective October 30, 2003. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of October 30, 2003. The 
incorporation by reference of certain other publications as listed in 
the regulations was approved previously by the Director of the Federal 
Register as of January 17, 2002 (67 FR 1, January 2, 2002), November 
12, 2002 (67 FR 65484, October 25, 2002), and July 7, 2003 (68 FR 
43033, June 6, 2003).

ADDRESSES: The service information referenced in this AD may be 
obtained from Pratt & Whitney, 400 Main St., East Hartford, CT 06108, 
telephone (860) 565-7700; fax (860) 565-1605. This information may be 
examined, by appointment, at the Federal Aviation Administration (FAA), 
New England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Diane Cook, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7133; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 2003-11-18, 
Amendment 39-13177 (68 FR 33844, June 7, 2003), which is applicable to 
PW model PW4050, PW4052, PW4056, PW4060, PW4060A, PW4060C, PW4062, 
PW4152, PW4156, PW4156A, PW4158, PW4160, PW4460, PW4462, and PW4650 
turbofan engines, was published in the Federal Register on July 21, 
2003 (68 FR 43033). That action proposed to mandate the same interim 
actions as AD 2003-11-18 (with some modifications based on AMOC 
approvals) to address engine takeoff power loss events, until the RCC 
rear HPC is incorporated in the PW4000 engines. That action also 
proposed to mandate the same terminating actions as

[[Page 56144]]

AD 2003-11-18, which incorporates the RCC rear HPC on engines installed 
in the Boeing fleet. That action also proposed to mandate the 
terminating actions to incorporate the RCC rear HPC on engines 
installed in the Airbus fleet.
    AD 2003-11-18 and the proposal noted that RCC rear HPC 
certification to 14 CFR part 25 was pending for engines installed in 
the McDonnell Douglas fleet. The AD and proposal noted that once 
certified, the terminating action requirements would be added for the 
McDonnell Douglas MD-11 fleet, by a superseding AD. Based on comments 
received on the proposal, and the recent 14 CFR part 25 certification 
for RCC rear HPC engines to be installed in McDonnell Douglas MD-11 
airplanes, this AD adds the terminating action requirements for the MD-
11 fleet.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. We received comments from four 
operators and one airframe manufacturer, who all agree with the 
technical aspects of the proposal, but have concerns with the 
procedural aspects of the proposal. Due consideration has been given to 
the comments received.

Typographical Error

    One commenter states there is a typographical error in proposal 
paragraph (u)(3)(ii). In that paragraph, August 31, 2007, should read 
August 31, 2006.
    The FAA agrees and has changed the final rule accordingly.

Request To Add Two Engine Manual References

    One commenter recommends adding the engine manual references of 
PW4000 EM 50A605, 71-00-00, Testing-21, dated June 15, 2003, and PW4000 
EM 50A822, 71-00-00, Testing-21, dated March 15, 2002, to paragraph 
(j)(2) of the proposal. The commenter states that this is needed to 
ensure that engines tested before the effective date of this 
superseding AD but after the effective date of AD 2003-11-18 are in 
compliance.
    The FAA does not agree. AD 2003-11-18 already requires Testing-21 
to be done in paragraph (j)(1) of the proposal, in accordance with the 
recommended references regardless if the testing was done before or 
after the effective date of AD 2003-11-18. Therefore, compliance is 
achieved, and no changes are made to the final rule based on this 
comment.

Undue Economic Burden

    Three commenters state that in general, when the FAA supersedes 
ADs, operators must review and revise engineering and maintenance 
program documentation because the superseded AD carries a new AD 
number. In this case, the commenters state that since the changes 
proposed in the NPRM are essentially changes to the effectivity, and 
not to any of the technical requirements, the expense to operators that 
results from this AD being superseded would create an undue economic 
burden. The commenters suggest that the FAA either delay issuing this 
AD until the McDonnell Douglas MD-11 terminating action can be 
included, in order to prevent yet another supersedure, or change the 
superseding AD to a revision to AD 2003-11-18, or issue separate ADs to 
cover the Airbus fleet and the McDonnell Douglas MD-11 fleet instead of 
combining all fleets into a single AD as proposed.
    The FAA does not agree. Almost a year ago the FAA announced that it 
would be adding required terminating action to the existing AD by 
superseding the AD as that terminating action was approved for use on 
engines installed in the various airplane fleets. The FAA received no 
comments regarding the use of that method of adding terminating action. 
When the FAA first superseded the AD to add required terminating action 
for engines installed in the Boeing fleet, no commenters objected and 
one commenter even stated that it expected the FAA to supersede the AD 
again once the terminating action was approved for use on engines 
installed in the Airbus and McDonnell Douglas fleets. Therefore, the 
FAA provided ample notice to operators of the intention to supersede 
the AD on multiple occasions. Including this action, the FAA has 
superseded a total of eight ADs while addressing the takeoff power 
surge condition in PW4000 engines. Therefore, the FAA does not agree 
that this additional supersedure will create an undue or unforeseen 
economic burden. The FAA does recognize, however, that by issuing an AD 
that supersedes a previous AD, rather than revising the previous AD, 
that operators may have to make additional entries in their maintenance 
records. This is a long-standing issue that pre-dates by many years 
this particular series of ADs addressing the PW4000 takeoff power surge 
issue. Approximately 13 years ago, in response to the desires of many 
operators who did not include a revision number in their maintenance 
documentation programs, the FAA established criteria for when we would 
issue an AD as a revision, thus keeping the root AD number the same, 
and when we would issue a superseding AD, thereby changing the AD 
number. Generally, the FAA issues a superseding AD when making a change 
to an instruction or referenced document that affects the substance of 
the required actions. Even though the applicability of each of the ADs 
in this series remained the same, supersedures were warranted as we 
made substantive changes to the regulatory requirements in each 
subsequent AD, for example, adding mandatory terminating action. 
Therefore, this AD remains as a supersedure, as proposed. In an effort 
to keep the economic burden on operators as low as possible, however, 
the FAA has decided to include in this final rule the mandatory 
terminating action for engines installed in McDonnell Douglas MD-11 
airplanes. Engines incorporating the RCC rear HPC were only recently 
approved for installation on McDonnell Douglas MD-11 airplanes. Since 
the original proposal to add mandatory terminating action contemplated 
that the RCC rear HPC would eventually be required for engines 
installed in the McDonnell Douglas MD-11 fleet, and since operators 
expected that the FAA would take that action, the FAA is adding that 
mandatory action to this final rule, in part, to avoid having to 
propose yet another superseding AD.

Paragraph Added To Allow Credit For RCC Incorporation

    Based on the potential for operators to have already incorporated 
the RCC rear HPC before the effective date of this AD, a paragraph has 
been added to the AD to allow credit for incorporating the RCC rear HPC 
before the effective date of the AD.
    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes described 
previously. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it would not have a substantial 
direct effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.

[[Page 56145]]

Accordingly, the FAA has not consulted with state authorities prior to 
publication of this final rule.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under the DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a 
significant economic impact, positive or negative, on a substantial 
number of small entities under the criteria of the Regulatory 
Flexibility Act. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
by contacting the Rules Docket at the location provided under the 
caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. Section 39.13 is amended by removing Amendment 39-13177 (68 FR 
33844, June 7, 2003) and by adding a new airworthiness directive, 
Amendment 39-13318, to read as follows:

2003-19-15 Pratt & Whitney: Docket No. 2000-NE-47-AD. Supersedes AD 
2003-11-18, Amendment 39-13177.

    Applicability: This airworthiness directive (AD) is applicable 
to: Pratt & Whitney (PW) models PW4050, PW4052, PW4056, PW4060, 
PW4060A, PW4060C, PW4062, PW4152, PW4156, PW4156A, PW4158, PW4160, 
PW4460, PW4462, and PW4650 turbofan engines. These engines are 
installed on, but not limited to, certain models of Airbus Industrie 
A300, Airbus Industrie A310, Boeing 747, Boeing 767, and McDonnell 
Douglas MD-11 series airplanes.

    Note 1: This AD applies to each engine identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For engines that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (u) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Compliance with this AD is required as indicated, 
unless already done.
    To prevent engine takeoff power losses due to high-pressure-
compressor (HPC) surges, do the following:
    (a) When complying with this AD, determine the configuration of 
each engine on each airplane using the following Table 1:

                                     Table 1.--Engine Configuration Listing
----------------------------------------------------------------------------------------------------------------
            Configuration                       Configuration                     Designator           Description
----------------------------------------------------------------------------------------------------- -------------
(1) Phase 1 without high pressure     A................................  Engines that did not
 turbine (HPT) 1st turbine vane cut                                       incorporate the Phase 3
 back stator (1TVCB).                                                     configuration at the time
                                                                          they were originally
                                                                          manufactured, or have not
                                                                          been converted to Phase 3
                                                                          configuration; and have not
                                                                          incorporated HPT 1TVCB
                                                                          using any Revision of
                                                                          service bulletin (SB)
                                                                          PW4ENG 72-514.
(2) Phase 1 with 1TVCB..............  B................................  Same as Configuration A
                                                                          except that HPT 1TVCB has
                                                                          been incorporated using any
                                                                          Revision of SB PW4ENG 72-
                                                                          514.
(3) Phase 3, 2nd Run................  C................................  Engines that incorporated
                                                                          the Phase 3 configuration
                                                                          at the time they were
                                                                          originally manufactured, or
                                                                          have been converted to the
                                                                          Phase 3 configuration
                                                                          during service; and that
                                                                          have had at least one HPC
                                                                          overhaul since new.
(4) Phase 3, 1st Run................  D................................  Same as Configuration C
                                                                          except that the engine has
                                                                          not had an HPC overhaul
                                                                          since new, except those
                                                                          engines that are defined as
                                                                          Configuration Designator G.
(5) HPC Cutback Stator Configuration  E................................  Engines that currently
 Engines.                                                                 incorporate any Revision of
                                                                          SBs PW4ENG 72-706, PW4ENG
                                                                          72-704, or PW4ENG 72-711.
(6) Engines that have passed Testing- F................................  Engines which have
 21.                                                                      successfully passed Testing-
                                                                          21 performed in accordance
                                                                          with paragraph (i) of this
                                                                          AD. Once an engine has
                                                                          passed a Testing-21, it
                                                                          will remain a Configuration
                                                                          F engine until the HPC is
                                                                          overhauled, or is replaced
                                                                          with a new or overhauled
                                                                          HPC, or the HPC is
                                                                          retrofitted to
                                                                          Configuration I.
(7) Phase 3, 1st Run Subpopulation    G................................  Engines that incorporated
 Engines. These engines are                                               the Phase 3 configuration
 identified by model and serial                                           and did not incorporate
 numbers (SNs) as follows:                                                Haynes material HPC inner
                                                                          case rear hook at the time
                                                                          they were originally
                                                                          manufactured, that were
                                                                          built from August 29, 1997
                                                                          up to the incorporation of
                                                                          the HPC inner rear case
                                                                          with Haynes material rear
                                                                          hook at the original engine
                                                                          manufacturer and have not
                                                                          had an HPC overhaul since
                                                                          new.
    PW4152: SN 724942 through SN
     724944 inclusive;
    PW4158: SN 728518 through SN
     728533 inclusive;
    PW4052, PW4056, PW4060, PW4060A,
     PW4060C, PW4062: SN 727732
     through SN 728000 inclusive and
     SN 729001 through SN 729010
     inclusive;
    PW4460, PW4462: SN 733813
     through SN 733840 inclusive.

[[Page 56146]]

 
(8) Engines from Configuration G      H................................  Engines that have
 that have passed Testing-21.                                             successfully passed Testing-
                                                                          21 performed in accordance
                                                                          with paragraph (i) of this
                                                                          AD. Once an engine has
                                                                          passed a Testing-21, it
                                                                          will remain a Configuration
                                                                          H engine until the HPC is
                                                                          overhauled, or is replaced
                                                                          with a new or overhauled
                                                                          HPC, or the HPC is
                                                                          retrofitted to
                                                                          Configuration I.
(9) Engines installed on Boeing,      I................................  Engines that have
 Airbus, or MD-11 airplanes with a                                        incorporated PW SB PW4ENG
 build standard that incorporates a                                       72-755, Revision 2, dated
 ring case configuration (RCC) rear                                       May 23, 2003; or Revision
 HPC.                                                                     3, dated September 16,
                                                                          2003; or PW SB PW4ENG 72-
                                                                          756, dated July 7, 2003; or
                                                                          Revision 1, dated September
                                                                          15, 2003; or PW SB PW4ENG
                                                                          72-759, dated July 7, 2003;
                                                                          or Revision 1, dated
                                                                          September 16, 2003; PW SB
                                                                          PW4ENG 72-757, Revision 1,
                                                                          dated September 15, 2003;
                                                                          or have been manufactured
                                                                          with an RCC rear HPC.
----------------------------------------------------------------------------------------------------------------

Configuration E Engines Installed on Boeing 747, 767, and McDonnell 
Douglas MD-11 Airplanes

    (b) For Configuration E engines, do the following:
    (1) Before further flight, limit the number of engines with 
Configuration E as described in Table 1 of this AD, to one on each 
airplane.
    (2) Remove all engines with Configuration E from service before 
accumulating 1,300 cycles-since-new (CSN) or cycles-since-conversion 
(CSC) to Configuration E, whichever is later.

Configuration G and H Engines Installed on Boeing 747, 767, McDonnell 
Douglas MD-11, and Airbus A300 and A310 Airplanes

    (c) For Configuration G and H engines installed on Boeing 747 
and 767, McDonnell Douglas MD-11, and Airbus A300 and A310 
airplanes, except as provided in paragraph (b) of this AD:
    (1) Before further flight, remove from service engines that 
exceed the CSN or cycles-since-Testing-21 (CST) limits listed in the 
following Table 2, or perform on-wing Testing-21 on Boeing 747 or 
McDonnell Douglas MD-11 airplanes in accordance with paragraph 
(i)(3) or (i)(4) respectively, of this AD. Thereafter, ensure that 
no Configuration G or H engines exceed the HPC CSN or CST limits 
listed in Table 2 of this AD.

                                                                             Table 2.--Configuration G and H Limits
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                      B767  PW4060  PW4060A                                 A300/310  PW4152
     Configuration designator             B747  PW4056               B767  PW4052               B767  PW4056             PW4060C  PW4062        MD-11  PW4460  PW4462        PW4156A  PW4158
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
G................................  1,700 CSN................  3,000 CSN................  2,100 CSN................  1,350 CSN...............  1,150 CSN...............  2,800 CSN.
H................................  600 CST..................  600 CST..................  600 CST..................  600 CST.................  600 CST.................  600 CST.
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------

    (2) Prior to return to service, Configuration G and H engines 
must meet the requirements of paragraph (i) of this AD.

Engines Installed on Boeing 767 and McDonnell Douglas MD-11 Airplanes

    (d) For engines installed on Boeing 767 and McDonnell Douglas 
MD-11 airplanes, except as provided in paragraph (b) and (c) of this 
AD:
    (1) Before further flight, limit the number of engines that 
exceed the HPC CSN, HPC cycles-since-overhaul (CSO), or HPC CST 
limits in Table 3 of this AD, to no more than one engine per 
airplane. Thereafter, ensure that no more than one engine per 
airplane exceeds the HPC CSN, CSO, or CST limit in Table 3 of this 
AD.
    (2) Prior to return to service, engines must meet the 
requirements of paragraph (i) of this AD.

Engines Installed on Boeing 747 Airplanes

    (e) Except as provided in paragraph (b) and (c) of this AD, 
before further flight, and thereafter, manage the engine 
configurations installed on Boeing 747 airplanes as follows:
    (1) Limit the number of Configuration A, B, C, or E engines that 
exceed the HPC CSN or HPC CSO limits listed in Table 3 of this AD, 
to not more than one engine per airplane. Table 3 follows:

                                                                          Table 3.--Engine Limits for Boeing Airplanes
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                                        B767  PW4060  PW4060A
      Configuration designator                B747  PW4056                    B767  PW4052                    B767  PW4056                 PW4060C  PW4062             MD-11  PW4460  PW4462
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
A..................................  1,400 CSN or CSO..............  3,000 CSN or CSO..............  1,600 CSN or CSO.............  900 CSN or CSO...............  800 CSN or CSO.
B..................................  2,100 CSN or CSO..............  4,400 CSN or CSO..............  2,800 CSN or CSO.............  2,000 CSN or CSO.............  1,200 CSN or CSO.
C..................................  2,100 CSO.....................  4,400 CSO.....................  2,800 CSO....................  2,000 CSO....................  1,300 CSO.
D..................................  2,600 CSN.....................  4,400 CSN.....................  3,000 CSN....................  2,200 CSN....................  2,000 CSN.
E..................................  750 CSN or CSO................  750 CSN or CSO................  750 CSN or CSO...............  750 CSN or CSO...............  750 CSN or CSO.
F..................................  800 CST.......................  800 CST.......................  800 CST......................  800 CST......................  800 CST.
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------

    (2) The single Configuration A, B, C, or E engine per airplane 
that exceeds the HPC CSN or CSO limits listed in Table 3 of this AD, 
must be limited to 2,600 HPC CSN or CSO for Configuration A, B, or C 
engines, or 1,300 HPC CSN or CSC to Configuration E, whichever is 
later, for Configuration E engines.

[[Page 56147]]

    (3) Remove from service or perform on-wing Testing-21 in 
accordance with paragraph (i)(3) of this AD for Configuration D 
engines, before accumulating 2,600 CSN.
    (4) Remove from service or perform on-wing Testing-21 in 
accordance with paragraph (i)(3) of this AD for Configuration F 
engines, before accumulating 800 CST.
    (5) Prior to return to service, Configuration A, B, C, D, and F 
engines must meet the requirements of paragraph (i) of this AD.

Engines Installed on Airbus A300 and A310 Airplanes

    (f) For Airbus operators that began operation of their A300 
fleet after the effective date of this AD, use paragraphs (f)(7) 
through (f)(9) of this AD to determine which Airbus A300 PW4158 
engine category 1 or 3 limits of the following Table 4 of this AD 
apply to your engine fleet. For Airbus operators that have been in 
operation before the effective date of this AD, use your PW4158 
engine category classification previously determined for your fleet 
and continue to apply the A300 PW4158 Category limits in Table 4 of 
this AD, to your fleet.

                                  Table 4.--Engine Limits for Airbus Airplanes
----------------------------------------------------------------------------------------------------------------
                                      A300 PW4158 Category
     Configuration  designator       1, and A310 PW4156 and   A300 PW4158 Category      A300 PW4158 Category 3
                                             PW4156A           2, and A310 PW4152
----------------------------------------------------------------------------------------------------------------
A..................................  900 CSN or CSO........  1,850 CSN or CSO......  500 CSN or CSO.
B..................................  2,200 CSN or CSO......  4,400 CSN or CSO......  1,600 CSN or CSO.
C..................................  2,200 CSO.............  4,400 CSO.............  1,600 CSO.
D..................................  4,400 CSN.............  4,400 CSN.............  4,400 CSN.
E..................................  Not Applicable........  Not Applicable........  Not Applicable.
F..................................  800 CST...............  800 CST...............  800 CST.
----------------------------------------------------------------------------------------------------------------

    (1) Determine the number of Group 3 Takeoff surges experienced 
by engines in your fleet before April 13, 2001. Count surge events 
for engines that had an HPC overhaul and incorporated either SB 
PW4ENG 72-484 or SB PW4ENG 72-575 at the time of overhaul. Do not 
count surge events for engines that did not have the HPC overhauled 
(i.e. 1st run engine) or had the HPC overhauled but did not 
incorporate either SB PW4ENG 72-484 or SB PW4ENG 72-575. See 
paragraph (s)(5) of this AD for a definition of a Group 3 Takeoff 
surge.
    (2) Determine the number of cumulative HPC CSO accrued by 
engines in your fleet before April 13, 2001. Count HPC CSO for 
engines that had an HPC overhaul and incorporated either SB PW4ENG 
72-484 or SB PW4ENG 72-575 at the time of overhaul. Do not count HPC 
CSO accrued on your engines while operating outside your fleet.
    (3) Calculate the surge rate by dividing the number of Group 3 
Takeoff surges determined in paragraph (f)(1) of this AD, by the 
number of cumulative HPC CSO determined in paragraph (f)(2) of this 
AD, and then multiply by 1,000.
    (4) If the surge rate calculated in paragraph (f)(3) of this AD 
is less than 0.005, go to paragraph (f)(5) of this AD. If the surge 
rate calculated in paragraph (f)(3) of this AD is greater than or 
equal to 0.005, go to paragraph (f)(6) of this AD.
    (5) If the cumulative HPC CSO determined in paragraph (f)(2) of 
this AD is greater than or equal to 200,000 cycles, use A300 PW4158 
Category 2 limits of Table 4 of this AD. If less than 200,000 
cycles, go to paragraph (f)(7) of this AD.
    (6) If the surge rate calculated in paragraph (f)(3) of this AD 
is greater than 0.035, use A300 PW4158 Category 3 limits of Table 4 
of this AD. If less than or equal to 0.035, go to paragraph (f)(7) 
of this AD.
    (7) Determine the percent of takeoffs with greater than a 1.45 
Takeoff engine pressure ratio (EPR) data for engines operating in 
your fleet. Count takeoffs from a random sample of at least 700 
airplane takeoffs that have occurred over at least a 3-month time 
period, for a period beginning no earlier than 23 months prior to 
the effective date of this AD. See paragraph (s)(6) of this AD for 
definition of Takeoff EPR data.
    (8) If there is insufficient data to satisfy the criteria of 
paragraph (f)(7) of this AD, use A300 PW4158 Category 3 limits of 
Table 4 of this AD.
    (9) If the percentage of takeoffs with greater than a 1.45 
Takeoff EPR data determined in paragraph (f)(7) of this AD is 
greater than 31%, use A300 PW4158 Category 3 limits listed in Table 
4 of this AD. If the percentage of takeoffs with greater than a 1.45 
Takeoff EPR data determined in paragraph (f)(7) of this AD is less 
than or equal to 31%, use A300 PW 4158 Category 1 limits listed in 
Table 4 of this AD.
    (g) For engines installed on Airbus A300 or A310 airplanes, 
except as provided in paragraph (c) of this AD, before further 
flight, limit the number of engines that exceed the CSN, CSO, or CST 
limits listed in Table 4 of this AD, to no more than one engine per 
airplane. Thereafter, ensure that no more than one engine per 
airplane exceeds the HPC CSN, CSO, or CST limits listed in Table 4 
of this AD. See paragraph (i) of this AD for return to service 
requirements.
    (h) For Airbus A300 PW4158 engine operators, except those 
operators whose engine fleets are determined to be Category 3 
classification based on surge rate in accordance with paragraph 
(f)(6) of this AD, re-evaluate your fleet category within 6 months 
from the last evaluation, and thereafter, at intervals not to exceed 
6 months, using the following criteria:
    (1) For operators whose engine fleets are initially classified 
as Category 1 or 3 in accordance with paragraph (f) of this AD, 
determine the percent of takeoffs with greater than a 1.45 Takeoff 
EPR data for engines operating in your fleet. Count takeoffs from a 
sample of at least 200 takeoffs that occurred over the most recent 
six month time period since the last categorization was determined, 
or the total number of takeoffs accumulated over 6 months if less 
than 200 takeoffs. See paragraph (s)(6) of this AD for definition of 
takeoff EPR data.
    (i) If there is insufficient data to satisfy the criteria of 
paragraph (h)(1) of this AD, use A300 PW4158 Category 3 limits 
listed in Table 4 of this AD.
    (ii) If the percentage of takeoffs with greater than a 1.45 
Takeoff EPR data determined in paragraph (h)(1) of this AD is 
greater than 31%, use A300 PW4158 Category 3 limits listed in Table 
4 of this AD.
    (iii) If the percentage of takeoffs with greater than a 1.45 
Takeoff EPR data determined in paragraph (h)(1) of this AD is less 
than or equal to 31%, use A300 PW4158 Category 1 limits listed in 
Table 4 of this AD.
    (2) For operators whose engine fleets are initially classified 
as Category 2 in accordance with paragraph (f) of this AD, determine 
the percent of takeoffs with greater than a 1.45 Takeoff EPR data 
for engines operating in your fleet. Count takeoffs from a sample of 
at least 200 takeoffs that occurred over the most recent six month 
time period since the last categorization was determined, or the 
total number of takeoffs accumulated over 6 months if less than 200 
takeoffs. See paragraph (s)(6) of this AD for definition of takeoff 
EPR data.
    (i) If there is insufficient data to satisfy the criteria of 
paragraph (h)(2) of this AD, use A300 PW4158 Category 3 limits 
listed in Table 4 of this AD.
    (ii) If the percentage of takeoffs with greater than a 1.45 
Takeoff EPR data determined in paragraph (h)(2) of this AD is 
greater than 37%, use A300 PW4158 Category 3 limits listed in Table 
4 of this AD.
    (iii) If the percentage of takeoffs with greater than a 1.45 
Takeoff EPR data determined in paragraph (h)(2) of this AD is 
greater than or equal to 21% and less than or equal to 37%, use A300 
PW4158 Category 1 limits listed in Table 4 of this AD.
    (iv) If the percentage of takeoffs with greater than a 1.45 
Takeoff EPR data determined in paragraph (h)(2) of this AD is less 
than 21%, use A300 PW4158 Category 2 limits listed in Table 4 of 
this AD.

[[Page 56148]]

Return to Service Requirements

    (i) Engines removed from service in accordance with paragraph 
(c), (d), (e), or (g) of this AD may be returned to service under 
the following conditions:
    (1) After passing a cool-engine fuel spike stability test 
(Testing-21) that has been done in accordance with PW4000 Engine 
Manual (EM) 50A605, 71-00-00, Testing-21, dated June 15, 2003; or 
PW4000 EM 50A443, 71-00-00, Testing-21, dated March 15, 2002; or 
PW4000 EM 50A822, 71-00-00, Testing-21, dated March 15, 2002; except 
for engines configured with Configuration E; or engines that have 
experienced a Group 3 takeoff surge; or
    (2) Engines tested before the effective date of this AD, in 
accordance with PW4000 EM 50A605, 71-00-00, Testing-21, dated March 
15, 2002; or PW4000 EM 50A443, 71-00-00, Testing-21, dated November 
14, 2001; or PW4000 EM 50A443, Temporary Revision No. 71-0026, dated 
November 14, 2001; or PW4000 EM 50A605, Temporary Revision No. 71-
0035, dated November 14, 2001; or PW4000 EM 50A822, 71-00-00, 
Testing-21, dated November 14, 2001; or PW4000 EM 50A822, Temporary 
Revision No. 71-0018, dated November 14, 2001; or PW Internal 
Engineering Notice (IEN) 96KC973D, dated October 12, 2001, meet the 
requirements of Testing-21; or
    (3) For PW4056 engines installed on Boeing 747 airplanes, after 
successfully completing on-wing Testing-21 in accordance with Major 
IEN 02KCW13E, dated November 21, 2002; or if done prior to the 
approval of Major IEN 02KCW13E, dated November 21, 2002; in 
accordance with Minor IENs 02KCW13, dated October 14, 2002; 
02KCW13A, dated October 14, 2002; 02KCW13C, dated July 25, 2002; or 
02KCW13D, July 29, 2002; except for engines configured with 
Configuration E, or engines that have experienced a Group 3 takeoff 
surge; or
    (4) For PW4460 and PW4462 engines installed on McDonnell Douglas 
MD-11 airplanes, after successfully completing on-wing Testing-21, 
in accordance with Major IEN 02KCW13H, dated December 9, 2002; or if 
done prior to the approval of Major IEN 02KCW13H, dated December 9, 
2002, in accordance with Minor IEN 02KCW13F, dated October 14, 2002; 
except for engines configured with Configuration E, or engines that 
have experienced a Group 3 takeoff surge; or
    (5) An engine that is either below or exceeds the limits of 
Table 3 or Table 4 of this AD may be removed and installed on 
another airplane without Testing-21, as long as the requirements of 
paragraph (c), (d), (e), or (g) of this AD are met at the time of 
engine installation.
    (6) An engine that has incorporated the RCC rear HPC in 
accordance with:
    (i) PW SB PW4ENG 72-755, Revision 3, dated September 16, 2003, 
for engines installed in Boeing airplanes, or
    (ii) PW SB PW4ENG 72-756, Revision 1, dated September 15, 2003, 
or PW SB PW4ENG 72-759, Revision 1, dated September 16, 2003, for 
engines installed in Airbus airplanes, or
    (iii) PW SB PW4ENG 72-757, Revision 1, dated September 15, 2003, 
for engines installed in McDonnell Douglas MD-11 airplanes; or
    (iv) RCC rear HPCs that were incorporated before the effective 
date this AD are allowed credit, in accordance with paragraph (t) of 
this AD.
    (v) Completing the SBs referenced in paragraphs (i)(6)(i) 
through (i)(6)(iii) of this AD changes the engine configuration to 
Configuration I.

Phase 0 or Phase 1, FB2T or FB2B Fan Blade Configurations

    (j) For Configuration A, B, C, D, E, F, G, and H engines with 
Phase 0 or Phase 1, FB2T or FB2B fan blade configurations complying 
with the requirements of AD 2001-09-05, (66 FR 22908, May 5, 2001); 
AD 2001-09-10, (66 FR 21853, May 2, 2001); or AD 2001-01-10, (66 FR 
6449, January 22, 2001); do the following:
    (1) Operators complying with the ADs listed in paragraph (j) of 
this AD using the weight restriction compliance method, must perform 
Testing-21 in accordance with paragraph (i) of this AD whenever any 
quantity of fan blades are replaced with new fan blades, overhauled 
fan blades, or with fan blades having the leading edges recontoured 
after the effective date of this AD, if during the shop visit the 
HPC is not overhauled and separation of a major engine flange, 
located between ``A'' flange and ``T'' flange, does not occur.
    (2) If an operator changes from the weight restriction 
compliance method to the fan blade leading edge recontouring method 
after the effective date of this AD, Testing-21 in accordance with 
paragraph (i) of this AD is required each time fan blade leading 
edge recontouring is done, if the fan blades accumulate more than 
450 cycles since new or since fan blade overhaul, or since the last 
time the fan blade leading edges were recontoured.

Minimum Build Standard

    (k) For engines to be installed on Boeing airplanes that are 
inducted into the shop after July 7, 2003; for engines to be 
installed on Airbus airplanes that are inducted into the shop after 
the effective date of this AD; and for engines to be installed on 
McDonnell Douglas MD-11 airplanes that are inducted into the shop 30 
days after the effective date of this AD:
    (1) Any Segmented Case Configuration (SCC) HPC module that is 
disassembled to a level that fully separates the HPC rear case 
assembly at H flange from the HPC module may not be returned to 
service unless the RCC rear HPC is incorporated in accordance with 
paragraphs (i)(6)(i) through (i)(6)(iii) of this AD.
    (2) Any engine with a SCC HPC module that is not disassembled in 
accordance with paragraph (k)(1) of this AD, must meet the following 
minimum build standard:
    (i) Do not install an engine with SCC HPC and HPT modules where 
the CSO of the HPC is 1,500 cycles or more than the CSN or CSO of 
the HPT.
    (ii) Any engine that undergoes separation of the SCC HPC and HPT 
modules must not be installed on an airplane unless it meets the 
build standard defined by PW SB PW4ENG 72-514. Engines that 
incorporate the Phase 3 configuration meet the build standard 
defined by PW SB PW4ENG 72-514.

Stability Testing Requirements

    (l) For engines to be installed on Boeing, Airbus, or McDonnell 
Douglas airplanes, after the effective date of this AD, Testing-21 
must be performed in accordance with paragraph (i) of this AD, 
before an engine can be returned to service after having undergone 
maintenance in the shop, except under any of the following 
conditions:
    (1) Engine HPC has incorporated the RCC rear HPC in accordance 
with paragraphs (i)(6)(i) through (i)(6)(iii) of this AD.
    (2) Engine maintenance intended to maintain the airworthiness of 
the engine between planned shop visits, that requires separation of 
a major engine flange located between ``A'' flange and ``T'' flange, 
that results in the engine being reassembled with all gas path-
related components remaining in the as-removed condition; or
    (3) Engines that successfully passed Testing-21 with zero CST, 
and are split at Flange E for transportation reasons as specified in 
the applicable Storage/Transport section of the applicable EM.

Thrust Rating Changes, Installation Changes, and Engine Transfers for 
Non-Configuration I Engines

    (m) When a thrust rating change has been made by using the 
Electronic Engine Control (EEC) programming plug, or an installation 
change has been made during an HPC overhaul period, use the lowest 
cyclic limit of Table 3 or Table 4 of this AD, associated with any 
engine thrust rating change or with any installation change made 
during this period. See paragraph (s)(2) for definition of HPC 
overhaul period.
    (n) When a PW4158 engine is transferred to another PW4158 engine 
operator whose engine fleet has a different category, use the lowest 
cyclic limit in Table 4 of this AD that was used or will be used 
during the affected HPC overhaul period.
    (o) When a PW4158 engine operator whose engine fleet changes 
category in accordance with paragraph (h) of this AD, use the lowest 
cyclic limits in Table 4 of this AD that were used or will be used 
during the affected HPC overhaul period.
    (p) Engines with an HPC having zero CSN or CSO at the time of 
thrust rating change, or installation change, or engine transfer 
between PW4158 engine operators, or subsequent change in operator 
engine fleet category in accordance with paragraph (h) of this AD in 
the direction of lower to higher Table 4 limits of this AD, are 
exempt from the lowest cyclic limit requirement in paragraphs (m), 
(n), and (o) of this AD.

Engines That Surge

    (q) For engines that experience a surge, and after 
troubleshooting procedures are completed for airplane-level surge 
during forward or reverse thrust, do the following:
    (1) For engines that experience a Group 3 takeoff surge, do the 
following:
    (i) Remove the engine from service before further flight and

[[Page 56149]]

    (ii) Incorporate the RCC rear HPC in accordance with paragraphs 
(i)(6)(i) through (i)(6)(iii) of this AD.
    (2) For any engine that experiences a forward or reverse thrust 
surge at EPR's greater than 1.25 that is not a Group 3 takeoff 
surge, do the following:
    (i) For Configuration A, B, C, D, F, G, and H engines, remove 
engine from service within 25 CIS or before further flight if 
airplane-level troubleshooting procedures require immediate engine 
removal, and perform Testing-21 in accordance with paragraph (i) of 
this AD, as applicable.
    (ii) For Configuration E engines, remove engine from service 
within 25 CIS or before further flight if airplane-level 
troubleshooting procedures require immediate engine removal.
    (3) Paragraphs (q)(1) and (q)(2) of this AD are not applicable 
to engines that incorporate the RCC rear HPC in accordance with 
paragraphs (i)(6)(i) through (i)(6)(iii) of this AD.

Terminating Action for Boeing, Airbus, and McDonnell Douglas MD-11 
Airplanes

    (r) For Boeing, Airbus, and McDonnell Douglas operators with 
PW4000 engines installed on Boeing 747, 767, Airbus A300, A310, or 
McDonnell Douglas MD-11 airplanes, modify the engine HPC assembly by 
incorporating the RCC rear HPC in accordance with (i)(6)(i) through 
(i)(6)(iii) of this AD, as follows:
    (1) For engines installed on Boeing 767 airplanes, manage the 
engine configuration installed on the airplanes in your fleet as 
follows:
    (i) By May 31, 2006 and thereafter, ensure that at least one 
Configuration I engine is installed on the airplane.
    (ii) After May 31, 2006, the non-Configuration I engine (SCC HPC 
module) installed on the airplane must have incorporated the Haynes 
material in the HPC inner case rear hook during the original engine 
build or during an HPC overhaul in accordance with PW4ENG 72-714, 
dated June 27, 2000; or Revision 1, dated November 8, 2001; or 
Revision 2, dated February 28, 2003; or SB PW4ENG 72-749, dated June 
17, 2002; or Revision 1, dated January 8, 2003; or Chromalloy 
Florida Repair procedure 00CFL-039-0, dated December 27, 2000.
    (2) For engines installed on Boeing 747 airplanes, manage the 
engine configuration installed on the airplanes in your fleet as 
follows:
    (i) By January 31, 2007 and thereafter, ensure that no more than 
one non-Configuration I engine is installed on the airplane.
    (ii) After January 31, 2007, the non-Configuration I engine (SCC 
HPC module) installed on the airplane must have incorporated the 
Haynes-material in the HPC inner case rear hook during the original 
build or during an HPC overhaul in accordance with SB PW4ENG 72-714, 
dated June 27, 2000; or Revision 1, dated November 8, 2001; or 
Revision 2, dated February 28, 2003; or SB PW4ENG 72-749, dated June 
17, 2002; or Revision 1, dated January 8, 2003; or Chromalloy 
Florida Repair procedure 00CFL-039-0, dated December 27, 2000.
    (3) For engines installed on Airbus A300, A310, or McDonnell 
Douglas MD-11 airplanes, manage the engine configuration installed 
on the airplanes in your fleet as follows:
    (i) By August 31, 2006 and thereafter, ensure that at least one 
Configuration I engine is installed on the Airbus A300 or A310 
airplane, and ensure that no more than one non-Configuration I 
engine is installed on the McDonnell Douglas MD-11 airplane.
    (ii) After August 31, 2006, the non-Configuration I engine 
installed on the airplane must have incorporated the Haynes-material 
in the HPC inner case rear hook during the original build or during 
an HPC overhaul in accordance with SB PW4ENG 72-714, dated June 27, 
2000; or Revision 1, dated November 8, 2001; or Revision 2, dated 
February 28, 2003; or SB PW4ENG 72-749, dated June 17, 2002; or 
Revision 1, dated January 8, 2003; or Chromalloy Florida Repair 
procedure 00CFL-039-0, dated December 27, 2000.
    (4) Prior to June 30, 2009, or whenever the HPC module is 
disassembled to a level that fully separates the HPC rear case 
assembly at H flange from the HPC module, whichever occurs first, 
incorporate the RCC rear HPC in accordance with paragraphs (i)(6)(i) 
through (i)(6)(iii) of this AD. Engines incorporating the RCC rear 
HPC are Configuration I engines. See paragraph (s)(7) of this AD for 
definition of HPC rear case assembly.
    (5) Incorporation of the RCC rear HPC constitutes terminating 
action to the Testing-21 requirements as specified in paragraph (l) 
of this AD, and engine stagger and or hard time limit requirements 
as specified in paragraphs (c), (d), (e) and (g) of this AD for 
engines installed on Boeing, Airbus, and McDonnell Douglas 
airplanes.

Definitions

    (s) For the purposes of this AD, the following definitions 
apply:
    (1) An HPC overhaul is defined as restoration of the HPC stages 
5 through 15 blade tip clearances to the limits specified in the 
applicable fits and clearances section of the engine manual.
    (2) An HPC overhaul period is defined as the time period between 
HPC overhauls.
    (3) An HPT overhaul is defined as restoration of the HPT stage 1 
and 2 blade tip clearances to the limits specified in the applicable 
fits and clearances section of the engine manual.
    (4) A Phase 3 engine is identified by a (-3) suffix after the 
engine model number on the data plate if incorporated at original 
manufacture, or a ``CN'' suffix after the engine serial number if 
the engine was converted using PW SBs PW4ENG 72-490, PW4ENG 72-504, 
or PW4ENG 72-572 after original manufacture.
    (5) A Group 3 takeoff surge is defined as the occurrence of any 
of the following engine symptoms that usually occur in combination 
during an attempted airplane takeoff operation (either at reduced, 
derated or full rated takeoff power setting) after takeoff power 
set, which can be attributed to no specific and correctable fault 
condition after completing airplane-level surge during forward 
thrust troubleshooting procedures:
    (i) Engine noises, including rumblings and loud ``bang(s).''
    (ii) Unstable engine parameters (EPR, N1, N2, and fuel flow) at 
a fixed thrust setting.
    (iii) Exhaust gas temperature (EGT) increase.
    (iv) Flames from the inlet, the exhaust, or both.
    (6) Takeoff EPR data is defined as Maximum Takeoff EPR if 
takeoff with Takeoff-Go-Around (TOGA) is selected, or Flex Takeoff 
EPR if takeoff with Flex Takeoff (FLXTO) is selected. Maximum 
Takeoff EPR or Flex Takeoff EPR may be recorded using any of the 
following methods:
    (i) Manually recorded by the flight crew read from the Takeoff 
EPR power management table during flight preparation (see Aircraft 
Flight Manual (AFM) chapter 5.02.00 and 6.02.01, or Flight Crew 
Operation Manual (FCOM) chapter 2.09.20) and then adjusted by adding 
0.010 to the EPR value recorded; or
    (ii) Automatically recorded during Takeoff at 0.18 Mach Number 
(Mn) (between 0.15 and 0.20 Mn is acceptable) using an aircraft 
automatic data recording system and then adjusted by subtracting 
0.010 from the EPR value recorded; or
    (iii) Automatically recorded during takeoff at maximum EGT, 
which typically occurs at 0.25-0.30 Mn, using an aircraft automatic 
data recording system.
    (7) HPC rear case assembly is defined as the HPC rear case with 
heat shields and other minor detail parts installed within the HPC 
rear case, but not including the HPC rear segmented stators.

Credit for Incorporating the RCC Rear HPC Before the Effective Date of 
This AD

    (t) Engines that have incorporated the RCC rear HPC before the 
effective date of this AD, in accordance with the following, comply 
with the RCC rear HPC incorporation requirements of this AD:
    (1) PW SB PW4ENG 72-755, Revision 3, dated September 16, 2003, 
or with PW SB PW4ENG 72-755, Revision 2, dated May 23, 2003 for 
engines installed in Boeing airplanes; or
    (2) PW SB PW4ENG 72-756, Revision 1, dated September 15, 2003, 
or PW SB PW4ENG 72-756, dated July 7, 2003, or PW SB PW4ENG 72-759, 
Revision 1, dated September 16, 2003, or PW SB PW4ENG 72-759, dated 
July 7, 2003, for engines installed in Airbus airplanes, or
    (3) PW SB PW4ENG 72-757, Revision 1, dated September 15, 2003, 
for engines installed in McDonnell Douglas airplanes.

Alternative Methods of Compliance

    (u) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Engine Certification Office (ECO). 
Operators must submit their request through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, ECO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the ECO.


[[Page 56150]]



Special Flight Permits

    (v) Special flight permits may be issued in accordance with 
Sec. Sec.  21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be done.

Testing-21 Reports

    (w) Within 60 days of test date, report the results of the cool-
engine fuel spike stability assessment tests (Testing-21) and on-
wing Testing-21 to the ANE-142 Branch Manager, Engine Certification 
Office, 12 New England Executive Park, Burlington, MA 01803-5299, or 
by electronic mail to [email protected]. Reporting 
requirements have been approved by the Office of Management and 
Budget and assigned OMB control number 2120-0056. Be sure to include 
the following information:
    (1) Engine serial number.
    (2) Engine configuration designation per Table 1 of this AD.
    (3) Date of the cool-engine fuel spike stability test or on-wing 
Testing-21, as applicable.
    (4) HPC Serial Number, and HPC time and cycles-since-new and 
since-compressor-overhaul at the time of the test.
    (5) Results of the test (Pass or Fail).

Documents That Have Been Incorporated By Reference

    (x) The actions must be done in accordance with the following 
Pratt and Whitney (PW) service bulletins (SBs), Internal Engineering 
Notice (IEN), Temporary Revisions, (TR's), engine manual (EM) 
sections, and Chromalloy Florida Repair Procedure:

----------------------------------------------------------------------------------------------------------------
             Document No.                       Pages                 Revision                   Date
----------------------------------------------------------------------------------------------------------------
PW SB PW4ENG 72-714..................  All...................  Original.............  June 27, 2000.
    Total pages: 12..................
PW SB PW4ENG 72-714..................  1-2...................  1....................  November 8, 2001.
                                       3.....................  Original.............  June 27, 2000.
                                       4.....................  1....................  November 8, 2001.
                                       5-12..................  Original.............  June 27, 2000.
    Total pages: 12..................
PW SB PW4ENG 72-714..................  All...................  2....................  February 28, 2003.
    Total pages: 14..................
PW SB PW4ENG 72-749..................  All...................  Original.............  June 17, 2002.
    Total pages: 14..................
PW SB PW4ENG 72-749..................  1.....................  1....................  January 8, 2003.
                                       2-4...................  Original.............  June 17, 2002.
                                       5-7...................  1....................  January 8, 2003.
                                       8.....................  Original.............  June 17, 2002.
                                       9-10..................  1....................  January 8, 2003.
                                       11....................  Original.............  June 17, 2002.
                                       12-14.................  1....................  January 8, 2003.
    Total pages: 14..................
PW SB PW4ENG 72-755..................  1.....................  2....................  May 23, 2003.
                                       2-37..................  1....................  April 8, 2003.
                                       38-39.................  2....................  May 23, 2003.
                                       40-54.................  1....................  April 8, 2003.
                                       55....................  2....................  May 23, 2003.
                                       56-152................  1....................  April 8, 2003.
                                       153...................  2....................  May 23, 2003.
                                       154-166...............  1....................  April 8, 2003.
                                       167-171...............  2....................  May 23, 2003.
                                       172-179...............  1....................  April 8, 2003.
                                       180-183...............  2....................  May 23, 2003.
                                       184-195...............  1....................  April 8, 2003.
                                       196...................  2....................  May 23, 2003.
                                       197-233...............  1....................  April 8, 2003.
                                       234...................  2....................  May 23, 2003.
                                       235-287...............  1....................  April 8, 2003.
    Total pages: 287.................
PW SB PW4ENG 72-755..................  1.....................  3....................  September 16, 2003.
                                       2.....................  1....................  April 8, 2003.
                                       3-294.................  3....................  September 16, 2003.
    Total pages: 294.................
PW SB PW4ENG 72-756..................  All...................  Original.............  July 7, 2003.
    Total pages: 283.................
PW SB PW4ENG 72-756..................  1.....................  1....................  September 15, 2003.
                                       2-4...................  Original.............  July 7, 2003.
                                       5-6...................  1....................  September 15, 2003.
                                       7-13..................  Original.............  July 7, 2003.
                                       14....................  1....................  September 15, 2003.
                                       15-48.................  Original.............  July 7, 2003.
                                       49....................  1....................  September 15, 2003.
                                       50-51.................  Original.............  July 7, 2003.
                                       52-64.................  1....................  September 15, 2003.
                                       65-109................  Original.............  July 7, 2003.
                                       110...................  1....................  September 15, 2003.

[[Page 56151]]

 
                                       111-123...............  Original.............  July 7, 2003.
                                       124...................  1....................  September 15, 2003.
                                       125-165...............  Original.............  July 7, 2003.
                                       166...................  1....................  September 15, 2003.
                                       167-172...............  Original.............  July 7, 2003.
                                       173...................  1....................  September 15, 2003.
                                       174-189...............  Original.............  July 7, 2003.
                                       190-192...............  1....................  September 15, 2003.
                                       193...................  Original.............  July 7, 2003.
                                       194-196...............  1....................  September 15, 2003.
                                       197-204...............  Original.............  July 7, 2003.
                                       205-206...............  1....................  September 15, 2003.
                                       207-224...............  Original.............  July 7, 2003.
                                       225...................  1....................  September 15, 2003.
                                       226-241...............  Original.............  July 7, 2003.
                                       242-243...............  1....................  September 15, 2003.
                                       244...................  Original.............  July 7, 2003.
                                       245...................  1....................  September 15, 2003.
                                       246-247...............  Original.............  July 7, 2003.
                                       248...................  1....................  September 15, 2003.
                                       249-255...............  Original.............  July 7, 2003.
                                       256-258...............  1....................  September 15, 2003.
                                       259-281...............  Original.............  July 7, 2003.
                                       282-283...............  1....................  September 15, 2003.
    Total pages: 283.................
PW SB PW4ENG 72-757..................  1.....................  1....................  September 15, 2003.
                                       2-3...................  Original.............  August 15, 2003.
                                       4.....................  1....................  September 15, 2003.
                                       5-34..................  Original.............  August 15, 2003.
                                       35....................  1....................  September 15, 2003.
                                       ......................  .....................  ..........................
                                       36-39.................  Original.............  August 15, 2003.
                                       40-57.................  1....................  September 15, 2003.
                                       58-105................  Original.............  August 15, 2003.
                                       106...................  1....................  September 15, 2003.
                                       107-147...............  Original.............  August 15, 2003.
                                       148...................  1....................  September 15, 2003.
                                       149-154...............  Original.............  August 15, 2003.
                                       155-156...............  1....................  September 15, 2003.
                                       157-167...............  Original.............  August 15, 2003.
                                       168...................  1....................  September 15, 2003.
                                       169-195...............  Original.............  August 15, 2003.
                                       196...................  1....................  September 15, 2003.
                                       197-218...............  Original.............  August 15, 2003.
                                       219-220...............  1....................  September 15, 2003.
                                       221-237...............  Original.............  August 15, 2003.
    Total pages: 237.................
PW SB PW4ENG 72-759..................  All...................  Original.............  July 7, 2003.
    Total pages: 228.................
PW SB PW4ENG 72-759..................  1.....................  1....................  September 16, 2003.
                                       2-4...................  Original.............  July 7, 2003.
                                       5-12..................  1....................  September 16, 2003.
                                       13-99.................  Original.............  July 7, 2003.
                                       100...................  1....................  September 16, 2003.
                                       101-134...............  Original.............  July 7, 2003.
                                       135...................  1....................  September 16, 2003.
                                       136-143...............  Original.............  July 7, 2003.
                                       144-146...............  1....................  September 16, 2003.
                                       147-174...............  Original.............  July 7, 2003.
                                       175...................  1....................  September 16, 2003.
                                       176-203...............  Original.............  July 7, 2003.
                                       204...................  1....................  September 16, 2003.
                                       205-224...............  Original.............  July 7, 2003.
                                       225-226...............  1....................  September 16, 2003.
                                       227...................  Original.............  July 7, 2003.
    Total pages: 227.................
PW IEN 02KCW13E......................  All...................  Original.............  November 21, 2002.
    Total pages: 20..................
PW IEN 02KCW13H......................  All...................  Original.............  December 9, 2002.
    Total pages: 21..................
PW IEN 96KC973D......................  All...................  Original.............  October 12, 2001.
    Total pages: 19..................
PW TR 71-0018........................  All...................  Original.............  November 14, 2001.

[[Page 56152]]

 
    Total pages: 24..................
PW TR 71-0026........................  All...................  Original.............  November 14, 2001.
    Total pages: 24..................
PW TR 71-0035........................  All...................  Original.............  November 14, 2001.
    Total pages: 24..................
PW4000 EM 50A443, 71-00-00, TESTING-   All...................  Original.............  March 15, 2002.
 21.
    Total pages: 20..................
PW4000 EM 50A605, 71-00-00, TESTING-   All...................  Original.............  March 15, 2002.
 21.
    Total pages: 20..................
PW4000 EM 50A605, 71-00-00,..........
TESTING-21...........................  1-7...................  Original.............  March 15, 2002.
                                       8-25..................  N/A..................  June 15, 2003.
    Total pages: 25..................
PW4000 EM 50A822, 71-00-00, TESTING-   All...................  Original.............  March 15, 2002.
 21.
    Total pages: 20..................
Chromalloy Florida Repair Procedure,
 00 CFL-039-0:
    Summary..........................  1-3...................  Original.............  December 27, 2000.
    Insp/chk-01......................  801...................  Original.............  December 27, 2000.
    Repair-01........................  901-903...............  Original.............  December 27, 2000.
        Total pages: 7...............
----------------------------------------------------------------------------------------------------------------

The incorporation by reference of PW SB PW4ENG 72-714, Revision 1, 
dated November 8, 2001, PW IEN 96KC973D, dated October 12, 2001; PW 
TR 71-0018, PW TR 71-0026, and PW TR 71-0035, all dated November 14, 
2001; was approved by the Director of the Federal Register as of 
January 17, 2002 (67 FR 1, January 2, 2002). The incorporation by 
reference of PW SB PW4ENG 72-749, dated June 17, 2002; PW4000 EM 
50A443, Section 71-00-00, Testing-21, dated March 15, 2002; PW4000 
EM 50A822, Section 71-00-00, Testing-21, dated March 15, 2002; 
PW4000 EM 50A605, Section 71-00-00, Testing-21, dated March 15, 
2002; and Chromalloy Florida Repair Procedure, 00 CFL-039-0, dated 
December 27, 2000; was approved by the Director of the Federal 
Register as of November 12, 2002 (67 FR 65484, October 25, 2002). 
The incorporation by reference of PW SB PW4ENG 72-714, Revision 2, 
dated February 28, 2003; PW SB PW4ENG 72-755, Revision 2, dated May 
23, 2003; PW SB PW4ENG 72-749, Revision 1, dated January 8, 2003; 
and PW EM 50A605, Section 71-00-00, Testing-21, dated June 15, 2003, 
was approved by the Director of the Federal Register as of July 7, 
2003 (68 FR 33844; June 6, 2003). The Director of the Federal 
Register approves the incorporation by reference of PW SB PW4ENG 72-
714, dated June 27, 2000; PW SB PW4ENG 72-755, Revision 3, dated 
September 16, 2003; PW SB PW4ENG 72-756, dated July 7, 2003; PW SB 
PW4ENG 72-756, Revision 1, dated September 15, 2003; PW SB PW4ENG 
72-757, Revision 1, dated September 15, 2003; PW SB PW4ENG 72-759, 
dated July 7, 2003; PW SB PW4ENG 72-759, Revision 1, dated September 
16, 2003; PW IEN 02KCW13E, dated November 21, 2002; and PW IEN 
02KCW13H, dated December 9, 2002, in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51. PW document copies may be obtained from Pratt and 
Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565-
7700; fax (860) 565-1605. Chromalloy Florida document copies may be 
obtained from Chromalloy Florida, 630 Anchors St., NW., Walton 
Beach, FL 32548; telephone (850) 244-7684; fax (850) 244-6322. 
Copies may be inspected at the FAA, New England Region, Office of 
the Regional Counsel, 12 New England Executive Park, Burlington, MA; 
or at the Office of the Federal Register, 800 North Capitol Street, 
NW, suite 700, Washington, DC.

Effective Date

    (y) This amendment becomes effective on October 30, 2003.

    Issued in Burlington, Massachusetts, on September 19, 2003.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 03-24486 Filed 9-29-03; 8:45 am]
BILLING CODE 4910-13-P

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