[Federal Register Volume 69, Number 91 (Tuesday, May 11, 2004)]
[Rules and Regulations]
[Pages 26015-26017]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-10374]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-273-AD; Amendment 39-13627; AD 2004-09-36]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all Boeing Model 727 series airplanes, that requires an 
inspection of the bolts used to attach the forward cone bolt to the 
engine flange to determine if the attachment bolts are either H-11 
steel bolts or cadmium-plated bolts. This action also requires 
replacement of either H-11 steel bolts or cadmium-plated bolts with new 
corrosion-resistant steel bolts. This action is necessary to prevent 
undetected cracking of the H-11 bolts or excessive wear of the cadmium-
plated bolts, which would compromise the primary load path of the 
engine support and could result in separation of the engine from the 
airplane. This action is intended to address the identified unsafe 
condition.

DATES: Effective June 15, 2004.
    The incorporation by reference of a certain publication listed in 
the regulations is approved by the Director of the Federal Register as 
of June 15, 2004.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the Federal 
Aviation Administration (FAA), Transport

[[Page 26016]]

Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, 
Washington; or at the National Archives and Records Administration 
(NARA). For information on the availability of this material at NARA, 
call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

FOR FURTHER INFORMATION CONTACT: Daniel F. Kutz, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6456; fax (425) 917-6590.

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 all Boeing Model 727 airplanes was 
published in the Federal Register on November 4, 2003 (68 FR 62408). 
That action proposed to require an inspection of the bolts used to 
attach the forward cone bolt to the engine flange to determine if the 
attachment bolts are either H-11 steel bolts or cadmium-plated bolts. 
That action also proposed to require replacement of either H-11 steel 
bolts or cadmium-plated bolts with new corrosion-resistant steel bolts.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Request To Allow Use of Alternative Part

    One commenter requests that the FAA revise the proposed AD to allow 
operators to use an alternative attachment bolt, part number (P/N) B27-
53-031-111. The commenter states that, in accordance with Supplemental 
Type Certificates (STC) SA5839NM and ST00350AT, some airplane engines 
are modified with a heavyweight hush kit, which uses bolts made with 
corrosion resistant Inconel 718. The commenter considers these bolts to 
satisfy the intent of the proposed AD.
    The FAA agrees. The AD does not specify what action should be taken 
if corrosion resistant bolts, P/N B27-53-031-111, are used to attach 
the forward cone bolt to the engine flange. Although these attachment 
bolts are not part of the original type design, allowing use of these 
attachment bolts in accordance with STC SA5839NM and ST00350AT will 
eliminate the need for an alternative method of compliance to the 
benefit of operators and the FAA. We have revised paragraph (a) of this 
AD accordingly.

Request To Extend Compliance Time

    The same commenter also requests that the we revise the proposed AD 
to extend the proposed compliance time for the inspection from ``18 
months or 3,000 cycles, whichever is earlier,'' to 24 months to allow 
affected operators sufficient time to perform the inspection and parts 
replacement during a regularly scheduled maintenance interval. The 
commenter states that the compliance time of the proposed AD presents 
an operational hardship in ensuring adequate time for the parts 
replacement, if necessary, during a regularly scheduled maintenance 
check. The commenter considers that the adoption of the proposed 
compliance time of 18 months would require operators to schedule 
special times to do the inspection, at additional expense and downtime.
    We do not agree with the commenter's request to extend the 
compliance time. In developing an appropriate compliance time for this 
action, we considered the safety implications and normal maintenance 
schedules for the timely accomplishment of the inspection and parts 
replacement. In consideration of these items, as well as the 
unpredictable nature of stress corrosion, we have determined that an 
18-month interval will ensure an acceptable level of safety and allow 
the inspection and parts replacement to be done during scheduled 
maintenance intervals for most affected operators.

Request To Withdraw the Proposed AD

    One commenter, on behalf of its members, requests that we withdraw 
the proposed AD. The commenter states that there are no reported 
failures of H-11 bolts, and that Stage 3 hushkits and the retirement of 
some Boeing Model 727 airplanes have significantly reduced the number 
of affected H-11 bolts. The commenter asserts that a maintenance 
program for inspection of the affected bolts would be sufficient for 
detecting cracking.
    We do not agree. Although we have not yet received any report of 
cracked H-11 bolts found on Boeing Model 727 airplanes, we have 
received a report that an operator found one cracked and two fractured 
H-11 bolts in the side load underwing fittings of a Model 767-200 
series airplane, as stated in AD 2002-10-51. We also point out that the 
nature of stress corrosion is unpredictable. Furthermore, we have 
determined that continued service for an unsafe condition for an 
unknown period of time conflicts with the intent of this AD. Thus we 
have not changed the final rule regarding this issue.

Request To Allow Repetitive Inspections Instead of Parts Replacement

    Another commenter requests that we revise the proposed AD to allow 
operators to perform repetitive inspections for cracking of H-11 bolts, 
instead of replacement of the H-11 bolts. The commenter states that, 
according to the proposed AD and the referenced service bulletin, there 
are no reported failures of H-11 bolts. The commenter also states that 
Stage 3 noise requirements and the retirement of some Boeing Model 727 
airplanes have significantly reduced the number of affected H-11 bolts. 
The commenter asserts that the replacement of H-11 bolts should not be 
a mandatory replacement, and that a revision to the maintenance program 
for inspection of the affected bolts would be sufficient for detecting 
cracking.
    We do not agree for the same reasons as stated above.

Conclusion

    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 previously 
described. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    There are approximately 1,148 Model 727 airplanes of the affected 
design in the worldwide fleet. The FAA estimates that 715 Model 727 
airplanes of U.S. registry will be affected by this AD, that it will 
take approximately 3 work hours per airplane to accomplish the required 
inspection, and that the average labor rate is $65 per work hour. Based 
on these figures, the cost impact of the AD on U.S. operators is 
estimated to be $139,425, or $195 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up,

[[Page 26017]]

planning time, or time necessitated by other administrative actions.

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

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 adding the following new airworthiness 
directive:

2004-09-36 Boeing: Amendment 39-13627. Docket 2002-NM-273-AD.

    Applicability: All Model 727, 727C, 727-100, 727-100C, 727-200, 
and 727-200F series airplanes, certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent undetected cracking of the H-11 bolts or excessive 
wear of the cadmium-plated bolts, which would compromise the primary 
load path of the engine support and could result in separation of 
the engine from the airplane, accomplish the following:

Inspection and Replacement

    (a) Within 18 months or 3,000 flight cycles from the effective 
date of this AD, whichever is earlier, inspect the bolts that are 
used to attach the forward cone bolt to the engine flange to 
determine if they are H-11 steel bolts (part number (P/N) 
BACB30GU12-64), cadmium-plated bolts (P/N BACB30LM12-64), or 
corrosion-resistant bolts (P/N NAS6712E64 or P/N B27-53-031-111, not 
listed in the service bulletin), per the Accomplishment Instructions 
of Boeing Alert Service Bulletin 727-71A0402, dated January 18, 
2001.
    (1) If corrosion-resistant bolts (P/N NAS6712E64 or P/N B27-53-
031-111) are installed, no further action is required by this 
paragraph.
    (2) If any H-11 steel bolt or cadmium-plated bolt is found, 
before further flight, replace the bolt with a new corrosion-
resistant bolt (P/N NAS6712E64), according to the Accomplishment 
Instructions in the service bulletin.

Parts Installation

    (b) As of the effective date of this AD, no person may install 
an H-11 steel bolt (P/N BACB30GU12-64) or a cadmium-plated bolt (P/N 
BACB30LM12-64) to attach the forward cone bolt to the engine flange 
on any airplane.

Alternative Methods of Compliance

    (c) In accordance with 14 CFR 39.19, the Manager, Seattle 
Aircraft Certification Office, FAA, is authorized to approve 
alternative methods of compliance (AMOCs) for this AD.

Incorporation by Reference

    (d) The actions shall be done in accordance with Boeing Alert 
Service Bulletin 727-71A0402, dated January 18, 2001. 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 Airplanes, 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 National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

Effective Date

    (e) This amendment becomes effective on June 15, 2004.

    Issued in Renton, Washington, on April 28, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-10374 Filed 5-10-04; 8:45 am]
BILLING CODE 4910-13-P