Airworthiness Directives; Pratt & Whitney JT9D-3A, -7, -7A, -7F, -7H, -7AH, and -7J Turbofan Engines

[Federal Register Volume 68, Number 250 (Wednesday, December 31, 2003)]
[Rules and Regulations]
[Pages 75400-75403]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-32155]



[[Page 75400]]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NE-52-AD Amendment 39-13410; AD 2003-24-12R1]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney JT9D-3A, -7, -7A, -7F, 
-7H, -7AH, and -7J Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: The FAA is revising an existing airworthiness directive (AD) 
for Pratt & Whitney (PW) JT9D-3A, -7, -7A, -7F, -7H, -7AH, and -7J 
turbofan engines, with gearbox pressure tube, part number (P/N) 697896, 
and No. 4 bearing front pressure manifold, P/N 670663, installed. That 
AD currently requires a one-time visual inspection of the gearbox 
pressure tube and No. 4 bearing front pressure manifold and the 
attaching clamp assemblies for correct positioning and for wear and 
damage, and replacement if necessary. This ad requires the same 
actions. This AD results from the need to correct errors in depicted 
clamping to ensure that AD compliance can be achieved, and to relax the 
level of maintenance required, as an optional method, when inspecting 
the affected tubing for dents. We are issuing this AD to prevent engine 
fires caused by failed gearbox pressure tubes or failed No. 4 bearing 
front pressure manifolds.

DATES: Effective December 18, 2003.
    We must receive any comments on this AD by March 1, 2004.

ADDRESSES:
    Use one of the following addresses to submit comments on this AD:
    [sbull] By mail: Federal Aviation Administration (FAA), New England 
Region, Office of the Regional Counsel, Attention: Rules Docket No. 
2003-NE-52-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
    [sbull] By fax: (781) 238-7055.
    [sbull] By e-mail: [email protected]
    You may examine the AD docket, by appointment, at the FAA, New 
England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT: Keith Lardie, Aerospace Engineer, 
Aircraft Certification Office, FAA, Engine and Propeller Directorate, 
12 New England Executive Park; telephone (781) 238-7189; fax (781) 238-
7199.

SUPPLEMENTARY INFORMATION: On November 25, 2003, the FAA issued AD 
2003-24-12, Amendment 39-13381 (68 FR 67585, December 3, 2003). That AD 
requires a one-time visual inspection of the gearbox pressure tube and 
No. 4 bearing front pressure manifold and the attaching clamp 
assemblies for correct positioning and for wear and damage, and 
replacement if necessary. That AD was the result of a report of a 
failed gearbox pressure tube that resulted in an engine fire. That 
condition, if not corrected, could result in engine fires caused by 
failed gearbox pressure tubes or failed No. 4 bearing front pressure 
manifolds.

Actions Since AD 2003-24-12 Was Issued

    Since that AD was issued, errors in the depicted clamping 
configuration have been found. The clamping configuration must be 
correct to ensure that AD compliance can be achieved. Also, an operator 
has requested that as an option to inspecting dented tubing by passing 
a ball bearing through the tube, to add dent depth limit criteria for 
each specific part number tube. The manufacturer supports this optional 
method and we have added it to the AD. This method avoids having to 
disconnect the tube from the engine.

FAA's Determination and Requirements of this AD

    The unsafe condition described previously is likely to exist or 
develop on other PW JT9D-3A, -7, -7A, -7F, -7H, -7AH, and -7J turbofan 
engines of the same type design. We are issuing this AD to prevent an 
engine fire caused by a failed gearbox pressure tube. This AD requires 
a one-time visual inspection of the gearbox pressure tube, P/N 697896, 
the No. 4 bearing front pressure manifold, P/N 670663, and the 
attaching clamp assemblies, P/Ns ST1594-06, ST1594-08, and ST1594-10, 
for correct positioning, for wear and damage, and replacement if 
necessary.

FAA's Determination of the Effective Date

    The effective date of this AD is the same as AD 2003-24-12. We 
discussed the errors depicted in AD 2003-24-12 with the U.S. operators, 
and adding the optional dent inspection method, and conclude that there 
is no adverse impact from using the same effective date.

Changes to 14 CFR Part 39--Effect on the AD

    On July 10, 2002, we issued a new version of 14 CFR part 39 (67 FR 
47998, July 22, 2002), which governs our AD system. This regulation now 
includes material that relates to special flight permits, alternative 
methods of compliance, and altered products. This material previously 
was included in each individual AD. Since this material is included in 
14 CFR part 39, we will not include it in future AD actions.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to submit any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. 2003-NE-52-AD'' in the 
subject line of your comments. If you want us to acknowledge receipt of 
your mailed comments, send us a self-addressed, stamped postcard with 
the docket number written on it; we will date-stamp your postcard and 
mail it back to you. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the rule 
that might suggest a need to modify it. If a person contacts us 
verbally, and that contact relates to a substantive part of this AD, we 
will summarize the contact and place the summary in the docket. We will 
consider all comments received by the closing date and may amend the AD 
in light of those comments.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications with you. You may get more information about plain 
language at http://www.faa.gov/language and http://www.plainlanguage.gov.

Examining the AD Docket

    You may examine the AD Docket (including any comments and service 
information), by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. See ADDRESSES for the 
location.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD 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.

[[Page 75401]]

    For the reasons discussed above, I certify that the regulation:
    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.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket No. 2003-NE-52-AD'' in your request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Accordingly, under 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. The FAA amends Sec.  39.13 by removing Amendment 39-13381 (68 FR 
67585, December 3, 2003), and by adding a new airworthiness directive, 
Amendment 39-13410, to read as follows:

2003-24-12R1 Pratt & Whitney: Amendment 39-13410. Docket No. 2003-
NE-52-AD. Revises AD 2003-24-12, Amendment 39-13381.

Effective Date

    (a) The effective date of this AD is the same as AD 2003-24-12, 
which is December 18, 2003.

Affected ADs

    (b) This AD revises AD 2003-24-12.

Applicability

    (c) This AD applies to Pratt & Whitney (PW) JT9D-3A, -7, -7A, -
7F, -7H, -7AH, and -7J turbofan engines, with gearbox pressure tube, 
part number (P/N) 697896, and No. 4 bearing front pressure manifold, 
P/N 670663, installed. These engines are installed on, but not 
limited to, Boeing 747-100, -200B, -200C, and -200F airplanes.

Unsafe Condition

    (d) This AD results from the need to correct errors in depicted 
clamping, to ensure that AD compliance can be achieved. The actions 
specified in this AD are intended to prevent engine fires caused by 
failed gearbox pressure tubes or failed No. 4 bearing front pressure 
manifolds.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within 250 hours-in-service or at the next shop visit, 
whichever occurs first, after the effective date of this AD, unless 
the actions have already been done.

One-Time Visual Inspection of Clamp Assemblies

    (f) Visually inspect the clamp assemblies, P/Ns ST1594-06, 
ST1594-08, and ST1594-10, (see Figure 1 of this AD) that attach the 
gearbox pressure tube and the No. 4 bearing front pressure manifold 
to the engine. Replace clamp assemblies before further flight that 
are rejected by any of the following rejection criteria:
    (1) Cracks, wear, or distortion in clamp metal.
    (2) Clamp cushions that are worn, compacted, cracked, coming 
apart in chunks, deteriorated, or missing. A reddish powder found 
around the clamp is an indication of deterioration.
BILLING CODE 4910-13-P

[[Page 75402]]

[GRAPHIC] [TIFF OMITTED] TR31DE03.004

BILLING CODE 4910-13-C

Visual Inspection of Gearbox Pressure Tube and No. 4 Bearing Front 
Pressure Manifold

    (g) If one or more clamp assemblies are rejected as described in 
paragraph (f) of this AD, or out of position or missing (see Figure 
1 of this AD), clean any debris and oil from the outer surface of 
the gearbox pressure tube and No. 4 bearing front pressure manifold 
and visually inspect the tube and manifold. Repair or replace the 
affected tube or manifold before further flight if it is rejected by 
any of the following rejection criteria:
    (1) Nicks, chafing, scratches, and or pitting 0.003 inch or 
greater in depth.
    (2) Dents within 0.25 inch of the ferrules or will not permit 
free passage of a ball having a minimum diameter of 80% of the 
tubing inner diameter.
    (3) Corrosion that is unable to be removed by a light polishing.
    (4) Tube or manifold is leaking oil.
    (5) As an option to the dent inspection method specified in 
paragraph (g)(2) of this AD, measure tube dent depth and use the 
following rejection criteria:
    (i) Dents in the gearbox pressure tube, P/N 697896, greater than 
0.055-inch depth.
    (ii) Dents in the No. 4 bearing front pressure manifold, P/N 
670663, forward of the tee fitting, greater than 0.100-inch depth.
    (iii) Dents in the No. 4 bearing front pressure manifold, PN 
670663, aft of the tee fitting, greater than 0.080-inch depth.

Gearbox Pressure Tube, No. 4 Bearing Front Pressure Manifold, and Clamp 
Assembly Positioning

    (h) Ensure that the gearbox pressure tube, No. 4 bearing front 
pressure manifold, and clamp assemblies are properly positioned, 
before further flight, as shown in Figure 1 of this AD.
    (i) Information on general inspection of these parts can be 
found in the Boeing 747 Aircraft Maintenance Manual, section 72-00-
00, and in PW Standard Practices Manual, P/N 585005.

Reporting Requirements

    (j) Report within 30 calendar days of the inspection, the 
results that equal or exceed the reject criteria to: Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7189; fax (781) 238-7199. Reporting requirements have been 
approved by the Office of Management and Budget control number 2120-
0056.

Alternative Methods of Compliance

    (k) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD if 
requested using the procedures found in 14 CFR 39.19.

Material Incorporated by Reference

    (l) None.

[[Page 75403]]

Related Information

    (m) None.

    Issued in Burlington, Massachusetts, on December 23, 2003.
Mark C. Fulmer,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 03-32155 Filed 12-30-03; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T04:08:51.773562+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

1780da6aaf445d6c03c40dce4aed8ae26e83b6758bd6dcbf353f54c6b9b7787a

Text SHA-256

4f965bfd480bf85df3370f707aa921cea56663c34edae6fd5bf5bab8100a72e8