[Federal Register: May 11, 2004 (Volume 69, Number 91)]
[Rules and Regulations]
[Page 26015-26017]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr11my04-12]
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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]
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