[Federal Register Volume 59, Number 101 (Thursday, May 26, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-12599]


[[Page Unknown]]

[Federal Register: May 26, 1994]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94-NM-60-AD; Amendment 39-8918; AD 94-11-02

 

Airworthiness Directives; Boeing Model 767 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to all Boeing Model 767 series airplanes. This action 
requires repetitive detailed visual and eddy current inspections to 
detect cracks of certain midspar fuse pins, and replacement of any 
cracked midspar fuse pin with a new fuse pin. This amendment is 
prompted by reports of longitudinal fatigue cracks on certain midspar 
fuse pins installed on Boeing Model 767 series airplanes. The actions 
specified in this AD are intended to prevent loss of the strut and 
engine due to cracking of both fuse pins on the same strut.

DATES: Effective June 10, 1994.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 10, 1994.
    Comments for inclusion in the Rules Docket must be received on or 
before July 25, 1994.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 94-NM-60-AD, 1601 Lind Avenue SW., Renton, 
Washington 98055-4056.
    The service information referenced in this AD may be obtained from 
Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 
98124-2207. This information may be examined at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at 
the Office of the Federal Register, 800 North Capitol Street NW., suite 
700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Transport Airplane Directorate, Seattle 
Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 
98055-4056; telephone (206) 227-2776; fax (206) 227-1181.

SUPPLEMENTARY INFORMATION: The FAA has received several reports of 
longitudinal fatigue cracks on certain midspar fuse pins installed on 
Boeing Model 767 series airplanes. A total of five cracked fuse pins 
have been found on two airplanes that had accumulated between 15,628 
and 23,056 total landings. Cracks were found on both midspar fuse pins 
of the same strut on one of these airplanes. A possible cause of this 
cracking is ovalization of the fuse pin due to stress. Results of 
testing of fuse pins having a design similar to those that cracked have 
revealed no significant reduction in shear strength with longitudinal 
cracks up to one inch in length. Cracking of both fuse pins on the same 
strut, if not corrected, could result in loss of the strut and engine.
    All reported cracks have occurred on midspar fuse pins having part 
number 311T3102-1. Midspar fuse pins having part numbers 311T3102-2 and 
311T2102-1 are similar in design to the fuse pins on which cracking was 
found and, therefore, also are subject to the addressed unsafe 
condition.
    The FAA has reviewed and approved Boeing Alert Service Bulletin 
767-54A0062, dated April 14, 1994, that describes procedures for 
repetitive detailed visual and eddy current inspections to detect 
cracks of certain midspar fuse pins, and replacement of any cracked 
midspar fuse pin with a new fuse pin. Accomplishment of these 
inspections will provide early detection of cracks in the midspar fuse 
pins of both struts.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other Model 767 series airplanes of the same type 
design, this AD is being issued to prevent cracking of both fuse pins 
on the same strut, which could result in loss of the strut and engine. 
This AD requires repetitive detailed visual and eddy current 
inspections to detect cracks of certain midspar fuse pins, and 
replacement of any cracked midspar fuse pin with a new fuse pin. The 
actions are required to be accomplished in accordance with the alert 
service bulletin described previously.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications shall identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 94-NM-60-AD.'' The postcard will be date stamped and 
returned to the commenter.
    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and is not a ``significant regulatory action'' 
under Executive Order 12866. It has been determined further that this 
action involves an emergency regulation under DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979). If it is determined 
that this emergency regulation otherwise would be significant under DOT 
Regulatory Policies and Procedures, a final regulatory evaluation will 
be prepared and placed in the Rules Docket. A copy of it, if filed, 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 14 CFR part 
39 of the Federal Aviation Regulations as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

    Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

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

94-11-02 Boeing: Amendment 39-8918 Docket 94-NM-60-AD.

    Applicability: All Model 767 series airplanes, certificated in 
any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent cracking of both fuse pins on the same strut, which 
could result in loss of the strut and engine, accomplish the 
following:
    (a) For airplanes having midspar fuse pins, part number 
311T3102-1: Perform a detailed visual inspection and an eddy current 
inspection to detect cracks of the midspar fuse pins, in accordance 
with Boeing Alert Service Bulletin 767-54A0062, dated April 14, 
1994, at the time specified in paragraph (a)(1), (a)(2), (a)(3), or 
(a)(4) of this AD, as applicable. Repeat these inspections 
thereafter at intervals not to exceed 3,000 landings.
    (1) For airplanes having midspar fuse pins that have accumulated 
18,000 or more total landings as of the effective date of this AD, 
accomplish the inspections within 60 days after the effective date 
of this AD.
    (2) For airplanes having midspar fuse pins that have accumulated 
15,000 or more total landings, but less than 18,000 total landings, 
as of the effective date of this AD, accomplish the inspections 
within 90 days after the effective date of this AD.
    (3) For airplanes having midspar fuse pins that have accumulated 
10,000 or more total landings, but less than 15,000 total landings, 
as of the effective date of this AD, accomplish the inspections 
within 120 days after the effective date of this AD.
    (4) For airplanes having midspar fuse pins that have accumulated 
less than 10,000 total landings as of the effective date of this AD, 
accomplish the inspections prior to the accumulation of 10,000 total 
landings on the fuse pin, or within 120 days after the effective 
date of this AD, whichever occurs later.
    (b) For airplanes having a midspar fuse pin, part number 
311T3102-2 or 311T2102-1: Prior to the accumulation of 15,000 total 
landings on the fuse pin, or within 90 days after the effective date 
of this AD, whichever occurs later, perform a detailed visual 
inspection and an eddy current inspection to detect cracks on the 
midspar fuse pins, in accordance with Boeing Alert Service Bulletin 
767-54A0062, dated April 14, 1994. Repeat these inspections 
thereafter at intervals not to exceed 3,000 landings.
    (c) If any crack is found during an inspection required by 
paragraph (a) or (b) of this AD, prior to further flight, replace 
the cracked midspar fuse pin with a new fuse pin, in accordance with 
Boeing Alert Service Bulletin 767-54A0062, dated April 14, 1994. 
Thereafter, perform the detailed visual and eddy current inspections 
specified in paragraph (a) or (b) of this AD, as applicable, on the 
new fuse pin at the time specified in paragraph (c)(1) or (c)(2) of 
this AD.
    (1) For airplanes having midspar fuse pins, part number 
311T3102-1: Perform the initial inspection of the new fuse pin prior 
to the accumulation of 10,000 total landings on the new fuse pin. 
Repeat the inspection thereafter at intervals not to exceed 3,000 
landings.
    (2) For airplanes having midspar fuse pins, part numbers 
311T3102-2 and 311T2102-1: Perform the initial inspection of the new 
fuse pin prior to the accumulation of 15,000 total landings on the 
new fuse pin. Repeat the inspection thereafter at intervals not to 
exceed 3,000 landings.
    (d) When any fuse pin is removed from a strut equipped with a 
General Electric engine, the engine must be removed in accordance 
with procedures described in the Boeing 767 Maintenance Manual, 
subject 71-00-02; or supported in accordance with a method approved 
by the Manager, Seattle Aircraft Certification Office (ACO), FAA, 
Transport Airplane Directorate.
    (e) When any fuse pin is removed from a strut equipped with a 
Pratt & Whitney engine, the engine must be removed in accordance 
with procedures described in the Boeing 767 Maintenance Manual, 
subject 71-00-02; or supported in accordance with procedures 
described in the Boeing 767 Maintenance Manual, subject 54-51-02, 
Temporary Revisions (TR), dated April 22, 1994; or supported in 
accordance with a method approved by the Manager, Seattle ACO, FAA, 
Transport Airplane Directorate.
    (f) When any fuse pin is removed from a strut equipped with a 
Rolls-Royce engine, the engine must be removed in accordance with 
procedures described in the Boeing 767 Maintenance Manual, subject 
71-00-02; or supported in accordance with procedures described in 
the Boeing 767 Maintenance Manual, subject 54-51-02; or supported in 
accordance with a method approved by the Manager, Seattle ACO, FAA, 
Transport Airplane Directorate.
    (g) Any midspar fuse pin, part number 311T3102-1, 311T3102-2, or 
311T2102-1, that has been removed from the strut and inspected for 
cracks using the 100 percent magnetic particle inspection technique 
described in Boeing Alert Service Bulletin 767-54A0062, dated April 
14, 1994, may be reinstalled on the strut provided that the fuse pin 
is found to be crack-free during the magnetic particle inspection. 
Prior to the accumulation of 3,000 total landings after 
reinstallation of the fuse pin, the fuse pin must be inspected in 
accordance with the requirements of paragraph (a) or (b) of this AD, 
as applicable.
    (h) 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, Seattle ACO, FAA, Transport 
Airplane Directorate. Operators shall submit their requests through 
an appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Seattle ACO.

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

    (i) 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 airplane to a location where 
the requirements of this AD can be accomplished.
    (j) The inspections and replacement shall be done in accordance 
with Boeing Alert Service Bulletin 767-54A0062, dated April 14, 
1994. 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 Boeing Commercial Airplane 
Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be 
inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
    (k) This amendment becomes effective on June 10, 1994.

    Issued in Renton, Washington, on May 18, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 94-12599 Filed 5-25-94; 8:45 am]
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