[Federal Register Volume 62, Number 103 (Thursday, May 29, 1997)]
[Rules and Regulations]
[Pages 28994-28995]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-13590]



[[Page 28994]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-ANE-26; Amendment 39-10034; AD 97-11-05]
RIN 2120-AA64


Airworthiness Directives; AlliedSignal Inc. ALF502 and LF507 
Series Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to AlliedSignal Inc. (formerly Textron Lycoming) ALF502 and 
LF507 series turbofan engines, that requires initial and repetitive on-
wing eddy current or in-shop fluorescent penetrant inspections of fuel 
manifold assemblies for cracks, and replacement, if necessary, with 
serviceable parts. In addition, this AD presents an optional 
terminating action to the repetitive inspections by replacing the fuel 
manifold assembly with an assembly of a new, improved design. This 
amendment is prompted by reports of cracking of the fuel manifold 
assembly at the No. 5 scallop location. The actions specified by this 
AD are intended to prevent cracking of the fuel manifold assembly, 
which could result in an engine fire.

DATES: Effective July 28, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 28, 1997.

ADDRESSES: The service information referenced in this AD may be 
obtained from AlliedSignal Aerospace, Attn: Data Distribution, M/S 64-
3/2101-201, P.O. Box 29003, Phoenix, AZ 85038-9003; telephone (602) 
365-2493, fax (602) 365-5577. This information may be examined at the 
Federal Aviation Administration (FAA), New England Region, Office of 
the Assistant Chief 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: Raymond Vakili, Aerospace Engineer, 
Los Angeles Aircraft Certification Office, FAA, Transport Airplane 
Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; telephone 
(310) 627-5262; fax (310) 627-5210.

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 AlliedSignal Inc. (formerly 
Textron Lycoming) ALF502 and LF507 series turbofan engines was 
published in the Federal Register on November 6, 1996 (61 FR 57342). 
That action proposed to require initial and repetitive on-wing eddy 
current inspection (ECI) and in-shop fluorescent penetrant inspection 
(FPI) of fuel manifold assemblies for cracks, and replacement, if 
necessary, with serviceable parts. In addition, that action proposed an 
optional terminating action to the repetitive inspections by replacing 
the fuel manifold assembly with an assembly of a new, improved design, 
Part Number (P/N) 2-163-620-37 or -38.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received from a single commenter (the manufacturer).
    The commenter states that inspection records reveal that cracks 
have been detected in fuel manifold assembly No. 5 scallop location 
only, and not, additionally, in No. 6, as stated in the NPRM. The FAA 
concurs and has deleted reference to the No. 6 location in this final 
rule.
    The commenter states that the applicability section listing of 
aircraft installations should be revised to more accurately describe 
the population of affected engines. The FAA concurs and has revised 
this final rule by including in the applicability section a reference 
to the list of affected fuel manifold P/Ns found in the manufacturer's 
service bulletin (SB).
    The commenter states that there should be separate inspection 
intervals for the ALF502R and LF507 series engines versus the ALF502L 
series, in order to better match the maintenance intervals stated in 
the FAA-approved Airworthiness Limitations Section. In addition, the 
commenter states that low-time engines need not be inspected until 
reaching 4,500 cycles since new (CSN). The FAA concurs. Accordingly, 
the FAA has revised the compliance section of this final rule by 
splitting the compliance requirements into two sub-paragraphs, one for 
ALF502L engines, and one for ALF502R and LF507 engines. In addition, 
the FAA has determined, based on a new risk analysis, that engines with 
less than 3,250 CSN on the effective date of the AD could now be 
inspected prior to reaching 4,500 CSN for ALF502R and LF507 engines, 
and 5,250 CSN for ALF502L engines. ALF502R and LF507 engines must still 
be inspected at intervals not to exceed 1,250 cycles in service (CIS) 
following the initial inspection, and ALF502L engines need repetitive 
inspections every hot section inspection (HSI) not to exceed 2,000 CIS. 
These changes allow the compliance intervals to better match the 
maintenance intervals stated in the FAA-approved Airworthiness 
Limitations Section.
    The commenter states that all the applicable fuel assembly P/Ns 
should be listed in the AD. The FAA does not concur. The P/Ns for fuel 
manifold assemblies affected by this AD are listed in the 
manufacturer's SB, which is incorporated by reference in the AD.
    The commenter states that a cracked fuel manifold assembly should 
be replaced with a serviceable assembly instead of only the new fuel 
manifold assembly, P/N 2-163-620-37 or -38, as stated in the NPRM. The 
manufacturer expressed concern regarding a shortage of spare parts 
should replacement of the defective manifold assemblies with the new 
fuel manifold assemblies, P/N 2-163-620-37 or -38, become mandatory. 
The manufacturer stated that the new fuel manifold assemblies, P/N 2-
163-620-37 or -38, are currently available for installation on 
production LF507 engines only. The FAA concurs. With the repetitive 
inspection procedures in place, an operator may continue replacing the 
cracked fuel manifold assemblies with serviceable fuel manifold 
assemblies. However, only replacement of a fuel manifold assembly with 
a newly improved fuel manifold assembly, P/N 2-163-620-37 or -38, will 
provide terminating action for the repetitive inspection requirements 
of this AD. This final rule has been changed accordingly.
    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.
    There are approximately 1,500 engines of the affected design in the 
worldwide fleet. The FAA estimates that 270 engines installed on 
aircraft of U.S. registry will be affected by this AD, that it will 
take approximately 2 work hours per engine per inspection to accomplish 
the ECI, 4 work hours per engine per inspection to accomplish the FPI, 
and that the average labor rate is $60 per work hour. Based on these 
figures, annual total cost impact of AD on U.S. operators is estimated 
to be $97,200 at

[[Page 28995]]

the estimated rate of one inspection per year.
    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.
    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:

97-11-05  AlliedSignal Inc.: Amendment 39-10034. Docket 96-ANE-26.

    Applicability: AlliedSignal Inc. (formerly Textron Lycoming) 
ALF502 and LF507 series turbofan engines with fuel manifold 
assemblies having Part Numbers (P/Ns) listed in paragraph 1(A) of 
AlliedSignal Service Bulletin (SB) No. ALF/LF 73-1002, dated 
December 22, 1995, installed on but not limited, British Aerospace 
Models BAe 146-100A, -200A, and -300A series; Avro International 
Models 146-RJ70A, -RJ85A, and -RJ100A series; and Canadair Model CL-
600-1A11 series aircraft.

    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 prevent cracking of the fuel manifold assembly, which could 
result in an engine fire, accomplish the following:
    (a) Perform initial and repetitive on-wing eddy current 
inspection (ECI) or in-shop fluorescent penetrant inspection (FPI) 
of fuel manifold assemblies having P/Ns listed in the paragraph 1.A 
of AlliedSignal Aerospace SB No. ALF/LF 73-1002, dated December 22, 
1995, for cracks, and replace, if necessary, with serviceable parts, 
in accordance with accomplishment instructions of this SB as 
follows:
    (1) For ALF502L series engines:
    (i) For fuel manifold assemblies with 3,250 or more cycles since 
new (CSN), or unknown CSN, on the effective date of this AD, inspect 
at the next hot section inspection (HSI), or 2,000 cycles in service 
(CIS) after the effective date of this AD, whichever occurs first.
    (ii) For fuel manifold assemblies with less than 3,250 CSN on 
the effective date of this AD, inspect at the next HSI, or prior to 
accumulating 5,250 CSN, whichever occurs first.
    (iii) Thereafter, inspect at HSI intervals not to exceed 2,000 
CIS since last inspection.
    (iv) If a fuel manifold assembly is found cracked, prior to 
further flight, replace with a serviceable assembly.
    (2) For ALF502R and LF507 series engines:
    (i) For fuel manifold assemblies with 3,250 or more CSN, or 
unknown CSN, on the effective date of this AD, inspect within 1,250 
CIS after the effective date of this AD.
    (ii) For fuel manifold assemblies with less than 3,250 CSN on 
the effective date of this AD, inspect prior to accumulating 4,500 
CSN.
    (iii) Thereafter, inspect at intervals not to exceed 1,250 CIS 
since last inspection.
    (iv) If a fuel manifold assembly is found cracked, prior to 
further flight, replace with a serviceable assembly.
    (b) Installation of a new, improved design fuel manifold 
assembly, P/N 2-163-620-37 or -38, constitutes terminating action to 
the inspection requirements of paragraph (a) of this AD.
    (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, Los Angeles Aircraft Certification 
Office. Operators shall forward their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Los Angeles Aircraft 
Certification Office.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the Los Angeles Aircraft Certification 
Office.

    (d) 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 requirements of this AD can be accomplished.
    (e) The actions required by this AD shall be done in accordance 
with the following AlliedSignal Aerospace SB:

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             Document No.                 Pages                Revision                         Date            
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ALF/LF 73-1002.......................          1-8  Original.....................  Dec. 22, 1995.               
    Total Pages: 8.                                                                                             
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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 AlliedSignal Aerospace, Attn: Data 
Distribution, M/S 64-3/2101-201, P.O. Box 29003, Phoenix, AZ 85038-
9003; telephone (602) 365-2493, fax (602) 365-5577. Copies may be 
inspected at the FAA, New England Region, Office of the Assistant 
Chief 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.
    (f) This amendment becomes effective on July 28, 1997.

    Issued in Burlington, Massachusetts, on May 15, 1997.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 97-13590 Filed 5-28-97; 8:45 am]
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