Airworthiness Directives; CFM International CFM56-2, -2A, -2B, -3, -3B, and -3C Series Turbofan Engines

[Federal Register Volume 65, Number 60 (Tuesday, March 28, 2000)]
[Rules and Regulations]
[Pages 16309-16311]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-6552]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NE-57-AD; Amendment 39-11632; AD 2000-05-22]
RIN 2120-AA64


Airworthiness Directives; CFM International CFM56-2, -2A, -2B, -
3, -3B, and -3C Series Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to CFM International CFM56-2, -2A, -2B, -3, -3B, and -3C 
series turbofan engines. This amendment requires a one-time eddy 
current inspection (ECI) for cracks in the bolt holes of high pressure 
turbine (HPT) front rotating air seals. This amendment is prompted by 
reports of machining anomalies in a bolt hole that led to an HPT front 
rotating air seal failure. The actions specified by this AD are 
intended to detect cracks in the bolt holes of HPT front rotating air 
seals, which can lead to an uncontained engine failure and damage to 
the aircraft.

DATES: Effective May 2, 2000.
    The incorporation by reference of certain publications in this rule 
is approved by the Director of the Federal Register as of May 2, 2000.

ADDRESSES: The service information referenced in this AD may be 
obtained from CFM International, Technical Publications Department, 1 
Neumann Way, Cincinnati, OH 45215; telephone (513) 552-2800, fax (513) 
552-2816. This information may be examined at the FAA, New England 
Region, Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA.

FOR FURTHER INFORMATION CONTACT: James Rosa, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7152, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to CFM International CFM56-2, -2A, -
2B, -3, -3B, and -3C Series Turbofan Engines was published in the 
Federal Register on December 13, 1999 (64 FR 69248). That action 
proposed to require a one-time eddy current inspection (ECI) for cracks 
in the bolt holes of high pressure turbine (HPT) front rotating air 
seals. That action was prompted by reports of machining anomalies in a 
bolt hole that led to an HPT front rotating air seal failure. That 
condition, if not corrected could result in cracks in the bolt holes of 
HPT front rotating air seals, which can lead to an uncontained engine 
failure and damage to the aircraft.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received.
    After careful review of the available data, the FAA has determined 
that air safety and the public interest require the adoption of the 
rule as proposed.

Economic Analysis

    There are approximately 121 engines of the affected design in the 
worldwide fleet. The FAA estimates that 13 engines installed on 
aircraft of US registry will be affected by this AD, that it would take 
approximately 300 work hours per engine to accomplish the actions, and 
that the average labor rate is $60 per work hour. Based on these 
figures, the

[[Page 16310]]

total cost impact of the AD on US operators is estimated to be 
$234,000.

Regulatory Impact

    The regulations adopted herein will 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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 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 
from 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

    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

    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]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

2000-05-22  CFM International: Amendment 39-11632. Docket 99-NE-57-
AD.

    Applicability: CFM International (CFMI) CFM56-2, -2A, -2B, -3, -
3B, and -3C series turbofan engines, installed on but not limited to 
McDonnell Douglas DC-8 series, Boeing 737 series, as well as Boeing 
E-3, E-6, and KC-135 (Military) series airplanes.

    Note 1: This airworthiness directive (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 (c) 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: Required as indicated, unless accomplished 
previously.
    To detect cracks in the bolt holes of high pressure turbine 
(HPT) front rotating air seals, which can lead to an uncontained 
engine failure and damage to the aircraft, accomplish the following:

One-Time Eddy Current Inspections (ECI) Based Upon Engine Model and 
Thrust Ratings

    (a) Perform a one-time ECI for cracks in the bolt holes of HPT 
front rotating air seals, part number 1282M72P03, and, if necessary, 
replace with serviceable parts, as follows:

CFM56-3 Series

    (1) For CFM56-3-B1 engine nameplate models with HPT front 
rotating air seals listed by serial number (S/N) in paragraph 
1.A(1), Effectivity, of CFMI CFM56-3/3B/3C Service Bulletin (SB) 72-
922, dated November 12, 1999, inspect in accordance with the 
procedures described in Paragraph 2, Accomplishment Instructions, of 
that SB, and in accordance with the intervals listed in paragraph 
(a)(4)(i) or (a)(4)(ii) of this AD, as applicable.
    (2) For CFM56-3B-2 models with maximum thrust limited to 20,100 
or 18,500 pounds by the flight management computer (FMC) and 
aircraft flight manual (AFM), with HPT front rotating air seals 
listed by S/N in paragraph 1.A(1), Effectivity, of CFMI CFM56-3/3B/
3C SB 72-922, dated November 12, 1999, inspect in accordance with 
the procedures described in Paragraph 2, Accomplishment 
Instructions, of that SB, and in accordance with the intervals 
listed in paragraph (a)(4)(i) or (a)(4)(ii) of this AD, as 
applicable.
    (3) For CFM56-3C-1 models with maximum thrust limited to 20,100 
or 18,500 pounds by the FMC and AFM, with HPT front rotating air 
seals listed by S/N in paragraph 1.A(1), Effectivity, of CFMI CFM56-
3/3B/3C SB 72-922, dated November 12, 1999, inspect in accordance 
with the procedures described in Paragraph 2, Accomplishment 
Instructions, of that SB, and in accordance with the intervals 
listed in paragraph (a)(4)(i) or (a)(4)(ii), as applicable.

Compliance Times for (a)(1), (a)(2), and (a)(3)

    (4) Use the following compliance times for the engine models 
listed in paragraphs (a)(1), (a)(2), and (a)(3) of this AD:
    (i) For HPT front rotating air seals with less than 10,000 
cycles since new (CSN) on the effective date of this AD, inspect at 
the next engine shop visit after accumulating 4,000 CSN, not to 
exceed 13,000 CSN.
    (ii) For HPT front rotating air seals with 10,000 CSN or more on 
the effective date of this AD, inspect at the next engine shop visit 
prior to accumulating 3,000 cycles-in-service (CIS) after the 
effective date of this AD, or prior to accumulating 20,000 CSN, 
whichever occurs first.
    (5) For CFM56-3B-2 engine nameplate models, with HPT front 
rotating air seals listed by S/N in paragraph 1.A(1), Effectivity, 
of CFMI CFM56-3/3B/3C SB 72-922, dated November 12, 1999, inspect in 
accordance with the procedures described in Paragraph 2, 
Accomplishment Instructions, of that SB, and in accordance with the 
intervals listed in paragraphs (a)(7)(i), or (a)(7)(ii) of this AD, 
as applicable.
    (6) For CFM56-3C-1 models with maximum thrust limited to 22,100 
pounds by the FMC and AFM, with HPT front rotating air seals listed 
by S/N in paragraph 1.A(1), Effectivity, of CFMI CFM56-3/3B/3C SB 
72-922, dated November 12, 1999, inspect in accordance with the 
procedures described in Paragraph 2, Accomplishment Instructions, of 
that SB, and in accordance with the intervals listed in paragraphs 
(a)(7)(i), or (a)(7)(ii) of this AD, as applicable.

Compliance Times for (a)(5) and (a)(6)

    (7) Use the following compliance times for the engine models 
listed in paragraphs (a)(5) and (a)(6) of this AD:
    (i) For HPT front rotating air seals with less than 9,800 CSN on 
the effective date of this AD, inspect at the next engine shop visit 
after accumulating 4,000 CSN, not to exceed 12,800 CSN.
    (ii) For HPT front rotating air seals with 9,800 CSN or more on 
the effective date of this AD, inspect at the next engine shop visit 
prior to accumulating 3,000 CIS after the effective date of this AD, 
or prior to accumulating 15,800 CSN, whichever occurs first.
    (8) For CFM56-3C-1 engine nameplate models, with HPT front 
rotating air seals listed by S/N in paragraph 1.A(1), Effectivity, 
of CFMI CFM56-3/3B/3C SB 72-922, dated November 12, 1999, inspect in 
accordance with the procedures described in Paragraph 2, 
Accomplishment Instructions, of that SB, as follows:
    (i) For HPT front rotating air seals with less than 9,100 CSN on 
the effective date of this AD, inspect at the next engine shop visit 
after accumulating 4,000 CSN, not to exceed 12,100 CSN.
    (ii) For HPT front rotating air seals with 9,100 CSN or more on 
the effective date of this AD, inspect at the next engine shop visit 
prior to accumulating 3,000 CIS after the effective date of this AD, 
or prior to accumulating 15,100 CSN, whichever occurs first.

Uninstalled Parts

    (9) Prior to installation in CFM56-3/3B/3C series engines, 
inspect uninstalled parts listed by S/N in paragraph 1.A(1), 
Effectivity, of CFMI CFM56-3/3B/3C SB 72-922, dated November 12, 
1999, in accordance with Paragraph 2, Accomplishment Instructions, 
of that SB.

CFM56-2 Series

    (10) For CFM56-2 engine nameplate models, with HPT front 
rotating air seals listed by S/N in paragraph 1.A(1), Effectivity,

[[Page 16311]]

of CFMI CFM56-2 SB 72-869, dated November 12, 1999, inspect in 
accordance with the procedures described in Paragraph 2, 
Accomplishment Instructions, of that SB, as follows:
    (i) For HPT front rotating air seals with less than 9,100 CSN on 
the effective date of this AD, inspect at the next engine shop visit 
after accumulating 4,000 CSN, not to exceed 10,100 CSN.
    (ii) For HPT front rotating air seals with 9,100 CSN or more on 
the effective date of this AD, inspect at the next engine shop visit 
prior to accumulating 1,000 CIS after the effective date of this AD, 
or prior to accumulating 13,100 CSN, whichever occurs first.

Uninstalled Parts

    (11) Prior to installation in CFM56-2 series engines, inspect 
uninstalled parts listed by S/N in paragraph 1.A(1), Effectivity, of 
CFMI CFM56-2 SB 72-869, dated November 12, 1999, in accordance with 
Paragraph 2, Accomplishment Instructions, of that SB.

CFM56-2A Series

    (12) For CFM56-2A engine nameplate models, with HPT front 
rotating air seals listed by S/N in paragraph 1.A(1), Effectivity, 
of CFM56-2A SB 72-470, dated November 12, 1999, inspect in 
accordance with the procedures described in Paragraph 2, 
Accomplishment Instructions, of that SB, after accumulating 3,000 
CSN but before accumulating 6,000 CSN.

Uninstalled Parts

    (13) Prior to installation in CFM56-2A series engines, inspect 
uninstalled parts listed by S/N in paragraph 1.A(1), Effectivity, of 
CFMI CFM56-2A SB 72-470, dated November 12, 1999, in accordance with 
the procedures described in Paragraph 2, Accomplishment 
Instructions, of that SB.

CFM56-2B Series

    (14) For CFM56-2B engine nameplate models, with HPT front 
rotating air seals listed by S/N in paragraph 1.A(1), Effectivity, 
of CFM56-2B SB 72-611, dated November 12, 1999, inspect in 
accordance with the procedures described in Paragraph 2, 
Accomplishment Instructions, of that SB, after accumulating 3,000 
CSN but before accumulating 6,000 CSN.

Uninstalled Parts

    (15) Prior to installation in CFM56-2B series engines, inspect 
uninstalled parts listed by S/N in paragraph 1.A(1), Effectivity, of 
CFMI CFM56-2B SB 72-611, dated November 12, 1999, in accordance with 
the procedures described in Paragraph 2, Accomplishment 
Instructions, of that SB.

Replace Cracked Parts

    (16) Prior to further flight, replace cracked HPT front rotating 
air seals with serviceable parts.

Definition

    (b) For the purpose of this AD, an engine shop visit is defined 
as the next time, after the effective date of this AD, an engine is 
in the shop for the purpose of maintenance or inspection.

Alternative Methods of Compliance

    (c) 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 shall 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 airworthiness directive, 
if any, may be obtained from the ECO.

Incorporation by Reference

    (d) The inspections shall be done in accordance with the 
following CFMI SB's: CFMI CFM56-3/3B/3C SB 72-922, dated November 
12, 1999; CFMI CFM56-2 SB 72-869, dated November 12, 1999; CFM56-2A 
SB 72-470, dated November 12, 1999, and CFM56-2B SB 72-611, dated 
November 12, 1999. This incorporation by reference was approved by 
the Director of the Federal Register in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51. Copies may be obtained from CFM 
International, Technical Publications Department, 1 Neumann Way, 
Cincinnati, OH 45215; telephone (513) 552-2800, fax (513) 552-2816. 
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.

Ferry Flights

    (e) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the aircraft to a location where 
the inspection requirements of this AD can be accomplished.
    (f) This amendment becomes effective on May 2, 2000.

    Issued in Burlington, Massachusetts, on March 7, 2000.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 00-6552 Filed 3-27-00; 8:45 am]
BILLING CODE 4910-13-U

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