[Federal Register Volume 70, Number 183 (Thursday, September 22, 2005)]
[Rules and Regulations]
[Pages 55524-55529]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-18783]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-66-AD; Amendment 39-14289; AD 2005-19-24]
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 supersedes an existing airworthiness directive 
(AD), applicable to all Boeing Model 727 series airplanes, that 
currently requires repetitive pre-modification inspections to detect 
cracks in the forward support fitting of the number 1 and number 3 
engines; and repair, if necessary. That AD also provides for an 
optional high frequency eddy current inspection, and, if possible, 
modification of the fastener holes; and various follow-on actions; 
which would terminate the repetitive pre-modification inspections. This 
amendment expands the area to be inspected; requires accomplishment of 
the previously optional (and subsequently revised) modification, which 
terminates certain repetitive inspections; and adds repetitive post-
modification inspections to detect cracking of the fastener holes, and 
corrective actions if necessary. The actions specified by this AD are 
intended to prevent fatigue cracking of the forward support fitting of 
the number 1 and number 3 engines, which could result in failure of the 
support fitting and consequent separation of the engine from the 
airplane. This action is

[[Page 55525]]

intended to address the identified unsafe condition.

DATES: Effective October 27, 2005.
    The incorporation by reference of Boeing Service Bulletin 727-
54A0010, Revision 6, including Appendix A, dated August 23, 2001, as 
listed in the regulations, is approved by the Director of the Federal 
Register as of October 27, 2005.
    The incorporation by reference of Boeing Service Bulletin 727-
54A0010, Revision 4, dated January 30, 1997, as listed in the 
regulations, was approved previously by the Director of the Federal 
Register as of March 18, 1997 (62 FR 9359, March 3, 1997).

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 Airplane Directorate, Rules 
Docket, 1601 Lind Avenue, SW., Renton, Washington.

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) by superseding AD 97-05-08, 
amendment 39-9952 (62 FR 9359, March 3, 1997), which is applicable to 
all Boeing Model 727 series airplanes, was published in the Federal 
Register on May 1, 2003 (68 FR 23231). The action proposed to continue 
to require repetitive pre-modification inspections to detect cracks in 
the forward support fitting of the number 1 and number 3 engines, and 
repair if necessary. The action also proposed to expand the area to be 
inspected; require accomplishment of the previously optional (and 
subsequently revised) modification, which would terminate certain 
repetitive inspections; and add repetitive post-modification 
inspections to detect cracking of the fastener holes, and corrective 
actions if necessary.

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.

Requests To Revise the Applicability

    One commenter requests that the applicability of the proposed AD be 
revised to apply only to Boeing Model 727 airplanes equipped with 
fittings having part number (P/N) 65-18722-xx. The commenter states 
that its Model 727-100 fleet does not include any airplanes equipped 
with fittings having that P/N. Because it changed the affected fittings 
during a re-engine modification in accordance with Supplemental Type 
Certificate (STC) SA8472SW, it was granted an alternate method of 
compliance (AMOC) for AD 97-05-08. The commenter asserts that revising 
the proposed applicability will prevent operators that do not have the 
affected fittings installed from having to request an AMOC for the 
requirements of the proposed AD.
    Another commenter requests that a statement be added to the 
proposed AD to exempt airplanes modified in accordance with STC 
SA4363NM. The commenter asserts that inclusion of this statement will 
make it perfectly clear to operators whether or not they are in 
compliance with the AD.
    We acknowledge the commenters' concern and, as we state in 
paragraph (t)(2) of this AD, AMOCs previously approved according to AD 
97-05-08 are acceptable for compliance with the corresponding 
requirements of this AD. These AMOCs address the commenter's concern. 
We find that no further clarifications are necessary and have made no 
change to the final rule in this regard.

Request To Add Language Specific to Airplanes With ``Hush Kit'' STCs 
Installed

    A third commenter requests that specific language be included in 
the final rule stating that airplanes modified in accordance with STCs 
SA3993NM, SA4833NM, SA5839NM, and ST00350AT may be inspected and 
modified in accordance with Boeing Service Bulletin 727-54A0010, 
Revision 6, without change. (Boeing Service Bulletin 727-54A0010, 
Revision 6, dated August 23, 2001, was referenced in the proposed AD as 
the appropriate source of service information for accomplishing the new 
actions). These STCs install noise suppression modification equipment 
(hush kits) on Model 727 airplanes. The commenter states that including 
this information in the AD, in lieu of making operators request AMOCs, 
will avoid confusion among operators with airplanes equipped with these 
STCs. The commenter submitted substantiating data to support its 
request.
    We do not agree. The static strength data analysis of the affected 
structure submitted was not sufficient to show that the commenter's 
request would result in an acceptable level of safety. Damage tolerance 
assessment is needed to determine if the inspections and modifications 
described in Boeing Service Bulletin 727-54A0010, Revision 6, are 
appropriate for airplanes modified in accordance with these STCs. In 
this case, the ability to inspect the affected area and changes in 
fatigue stress levels need to be addressed. Additionally, the 
inspections and modifications specified in the service bulletin 
specifically address only affected original equipment manufacturer 
configurations. However, as we explained previously, we will consider 
requests for AMOCs submitted with sufficient technical justification to 
support the request. We have made no change to the final rule regarding 
this issue.

Request To Change the Method of Inspection

    Another commenter, the manufacturer, requests that we revise 
paragraphs (d)(1) and (d)(3) of the proposed AD to revise the method of 
inspection. Specifically, the commenter recommends revising ``* * * If 
any corrosion is found, before further flight, remove the corrosion in 
accordance with Figure 5 of the service bulletin, and perform a general 
visual inspection to detect cracking * * *'' to read ``* * * If any 
corrosion is found, before further flight, remove the corrosion in 
accordance with Figure 5 of the service bulletin, and perform a HFEC 
inspection to detect cracking * * *.'' The commenter asserts that the 
high frequency eddy current (HFEC) inspection is a better method than a 
surveillance inspection and will provide an adequate level of safety by 
enabling operators to find small cracks.
    We partially agree with the commenter. We find that an HFEC 
inspection should be accomplished after removal of corrosion. However, 
we do not agree that it is necessary to revise paragraphs (d)(1) and 
(d)(3) of this final rule as requested. Paragraphs (d)(1) and (d)(3) 
require any corrosion found to be removed in accordance with Figure 5 
of Boeing Service Bulletin 727-54A0010, Revision 6, dated August 23, 
2001. Step 5 of Figure 5 of the service bulletin includes procedures 
for doing an HFEC inspection for cracks and repairing any cracks found 
once the corrosion has been identified and removed from the affected 
area. The general visual inspection required by paragraphs (d)(1) and 
(d)(3) follows the instructions given in Figure 1, Step 2, of the 
service bulletin. We find that no change to the final rule is necessary 
regarding this issue.

[[Page 55526]]

Request To Refer Specifically to Post-Modification Inspections

    The same commenter also requests that paragraph (m) of the proposed 
AD be revised to refer to the post-modification inspections in Revision 
5 of Boeing Alert Service Bulletin 727-54A0010, dated February 15, 
2001. Specifically, the commenter recommends revising ``* * * 
Inspections done before the effective date of this AD in accordance 
with Boeing Alert Service Bulletin 727-54A0010, Revision 5, dated 
February 15, 2001, are acceptable for compliance with the corresponding 
inspection requirements of this paragraph * * *.'' to ``* * * 
Inspections done before the effective date of this AD in accordance 
with Part III of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 727-54A0010, Revision 5, dated February 15, 2001, are 
acceptable for compliance with the corresponding inspection 
requirements of this paragraph * * *.'' The commenter believes that, 
for airplanes that have accomplished the modification, only the repeat 
post-modification inspection requirements of Revision 5 of the service 
bulletin provide an equivalent level of safety for the fleet.
    We agree with the request for the reason provided by the commenter. 
It was our intent to refer specifically to Part III of the 
Accomplishment Instructions of Revision 5 of the service bulletin in 
paragraph (m). Therefore, we have revised paragraph (m) of this final 
rule to specifically refer to Part III of the Accomplishment 
Instructions of Revision 5 of the service bulletin for accomplishment 
of post-modification inspections done before the effective date of the 
AD.

Explanation of Additional Changes to the Proposed AD

    Boeing has received a Delegation Option Authorization (DOA). We 
have revised this final rule to delegate the authority to approve an 
alternative method of compliance for any repair required by this AD to 
the Authorized Representative for the Boeing DOA Organization rather 
than the Designated Engineering Representative (DER). Accordingly, we 
have added paragraph (t)(3) to this final rule and revised the wording 
of paragraphs (h)(1) and (i) of this AD. We have also revised the 
wording of paragraph (t)(1) of this final rule (specified as paragraph 
(s)(1) in the proposed AD) for reasons discussed under ``Changes to 14 
CFR part 39/Effect on the AD.''
    Because the language in Note 6 of the proposed AD is regulatory in 
nature, that note has been redesignated as paragraph (r) of this final 
rule. We have re-identified subsequent notes and paragraphs 
accordingly.

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.

Changes to 14 CFR Part 39/Effect on the AD

    On July 10, 2002, the FAA issued a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness 
directives system. The regulation now includes material that relates to 
altered products, special flight permits, and AMOCs. Because we have 
now included this material in part 39, only the office authorized to 
approve AMOCs is identified in each individual AD. However, for clarity 
and consistency in this final rule, we have retained the language of 
the NPRM regarding that material, except for the revisions to certain 
language discussed previously.

Change to Labor Rate Estimate and Airplane Fleet Data

    We have reviewed the figures we have used over the past several 
years to calculate AD costs to operators. To account for various 
inflationary costs in the airline industry, we find it necessary to 
increase the labor rate used in these calculations from $60 per work 
hour to $65 per work hour. The cost impact information, below, reflects 
this increase in the specified hourly labor rate.
    We have also revised the cost impact information to more accurately 
describe the number of airplanes of the affected design in the current 
worldwide and U.S. fleets.

Cost Impact

    There are approximately 1,009 airplanes of the affected design in 
the worldwide fleet. The FAA estimates that 587 airplanes of U.S. 
registry will be affected by this AD.
    We provide the following cost estimates for this AD:

----------------------------------------------------------------------------------------------------------------
                                                     Average
               Action                 Work  hours   labor rate    Cost of      Cost per      Cost for the U.S.
                                                     per hour      parts       airplane            fleet
----------------------------------------------------------------------------------------------------------------
AD 97-05-08 inspections, per                    2          $65           $0         $130  $76,310, per
 inspection cycle.                                                                         inspection cycle.
Inspections before structural                  14           65            0          910  534,170, per
 rework, per inspection cycle.                                                             inspection cycle.
Structural rework...................            7           65        7,875        8,330  4,889,710.
Inspections after structural rework,           12           65            0          780  457,860, per
 per inspection cycle.                                                                     inspection cycle.
----------------------------------------------------------------------------------------------------------------

    The cost impact figures discussed above are 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, 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

[[Page 55527]]

``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 removing amendment 39-9952 (62 FR 9359, 
March 3, 1997), and by adding a new airworthiness directive (AD), 
amendment 39-14289, to read as follows:

2005-19-24 Boeing: Amendment 39-14289. Docket 2002-NM-66-AD. 
Supersedes AD 97-05-08, Amendment 39-9952.

    Applicability: All Model 727 series airplanes, certificated in 
any category.

    Note 1: This AD applies to each airplane 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 airplanes 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 (t)(1) 
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 fatigue cracking of the forward support fitting of 
the number 1 and number 3 engines, which could result in failure of 
the support fitting and consequent separation of the engine from the 
airplane, accomplish the following:

Restatement of Requirements of AD 97-05-08

Inspections

    (a) Within 100 days or 600 flight cycles after March 18, 1997 
(the effective date of AD 97-05-08, amendment 39-9952), whichever 
occurs first, accomplish paragraphs (a)(1), (a)(2), and (a)(3) of 
this AD, in accordance with Boeing Service Bulletin 727-54A0010, 
Revision 4, dated January 30, 1997.
    (1) Perform a visual inspection to detect cracks of the upper 
and lower flanges, and the vertical web of the forward support 
fitting of the number 1 and number 3 engines, in accordance with 
Part 1--Pre-Modification Inspections of the Accomplishment 
Instructions of the service bulletin.
    (2) Perform a high frequency eddy current (HFEC) inspection to 
detect cracks of the forward flange of the support fitting adjacent 
to the collars of two fasteners of the number 1 and number 3 
engines, in accordance with Part 1--Pre-Modification Inspections of 
the Accomplishment Instructions of the service bulletin.
    (3) Perform a detailed inspection to detect cracks of the upper 
and lower flanges adjacent to six fasteners of the fitting of the 
number 1 and number 3 engines, in accordance with Part 1--Pre-
Modification Inspections of the Accomplishment Instructions of the 
service bulletin.

    Note 2: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''


    (b) If no crack is detected during the inspections required by 
paragraph (a) of this AD, repeat those inspections thereafter at 
intervals not to exceed 100 days or 600 flight cycles, whichever 
occurs first, until the initial inspections required by paragraph 
(d) of this AD have been accomplished.
    (c) If any crack is detected during any inspection required by 
paragraph (a) of this AD, prior to further flight, repair the 
forward support fitting in accordance with a method approved by the 
Manager, Seattle Aircraft Certification Office (ACO), FAA.

New Requirements of This AD

    Note 3: Where there are differences between the service bulletin 
and this AD, this AD prevails.

Inspections: All Airplanes

    (d) For all airplanes: Within 600 flight cycles or 100 days 
after the effective date of this AD, whichever occurs first, inspect 
the forward support fitting of the number 1 and number 3 engines, as 
specified in paragraphs (d)(1), (d)(2), (d)(3), (d)(4), and (d)(5) 
of this AD, in accordance with Part I of the Accomplishment 
Instructions of Boeing Service Bulletin 727-54A0010, Revision 6, 
dated August 23, 2001. Accomplishment of these initial inspections 
terminates the inspection requirements of paragraphs (a) and (b) of 
this AD.
    (1) Perform a general visual inspection to detect corrosion and 
cracking of the fittings in areas inboard of the side of the body, 
in accordance with Figure 1 of the service bulletin. If any 
corrosion is found, before further flight, remove the corrosion by 
accomplishing all of the actions in and in accordance with Figure 5 
of the service bulletin, and then perform a general visual 
inspection to detect cracking of the area, in accordance with the 
service bulletin.

    Note 4: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
ensure visual access to all surfaces in the inspection area. This 
level of inspection is made under normally available lighting 
conditions such as daylight, hangar lighting, flashlight, or 
droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''

    (2) Perform an HFEC inspection to detect cracking of the upper 
and lower horizontal flanges and post tangs of the fittings from 
inside the airplane, in accordance with Figure 1 of the service 
bulletin.
    (3) Perform a general visual inspection to detect cracking and 
corrosion of the fittings in areas outboard of the side of the body, 
in accordance with Figure 1 of the service bulletin. If any 
corrosion is found, before further flight, remove the corrosion by 
accomplishing all of the actions in and in accordance with Figure 5 
of the service bulletin, and perform a general visual inspection to 
detect cracking of the area, in accordance with the service 
bulletin.
    (4) Perform a detailed inspection to detect cracking and 
corrosion of the web in areas outboard of the side of the body, in 
accordance with Figure 1 of the service bulletin. If any corrosion 
is found, before further flight, remove the corrosion in accordance 
with Figure 5 of the service bulletin, and perform thickness 
measurements and detailed and HFEC inspections of the vertical web 
inboard and outboard of the side of the body to detect corrosion and 
cracking, in accordance with Figure 2 of the service bulletin. If 
the web thickness is less than 0.130 inch, do paragraph (i) of this 
AD.
    (5) Perform detailed and HFEC inspections to detect cracking of 
the upper and lower horizontal flanges at the side of the body, in 
accordance with Figure 1 of the service bulletin.

Additional Inspections: Group 2 Airplanes

    (e) For Group 2 airplanes, as identified in Boeing Service 
Bulletin 727-54A0010, Revision 6, dated August 23, 2001: Within 600 
flight cycles or 100 days after the effective date of this AD, 
whichever occurs first, inspect the forward support fitting of the 
number 1 and number 3 engines at the

[[Page 55528]]

firewall to detect cracking, as specified in paragraphs (e)(1), 
(e)(2), (e)(3), and (e)(4) of this AD, in accordance with Part I of 
the Accomplishment Instructions of the service bulletin.
    (1) Perform a detailed inspection to detect cracking of the aft 
side of the upper horizontal flange, in accordance with Figure 1 of 
the service bulletin.
    (2) Perform a low frequency eddy current (LFEC) or an open hole 
HFEC inspection to detect cracking of the aft side of the upper 
horizontal flange, in accordance with Figure 1 of the service 
bulletin.
    (3) Perform a detailed inspection to detect cracking of the aft 
side of the lower horizontal flange, in accordance with Figure 1 of 
the service bulletin.
    (4) Perform an HFEC inspection to detect cracking of the aft 
side of the lower horizontal flange, in accordance with Figure 1 of 
the service bulletin.

No Cracking Found: Follow-on Inspections, All Airplanes

    (f) For all airplanes: If no cracking is found during any 
inspection required by paragraph (d) of this AD, repeat the 
applicable inspections within the applicable intervals specified in 
paragraph 1.E., Table 1, of Boeing Service Bulletin 727-54A0010, 
Revision 6, dated August 23, 2001, until the modification required 
by paragraph (j) of this AD has been done.

No Cracking Found: Additional Follow-on Inspections, Group 2 Airplanes

    (g) For Group 2 airplanes only: If no cracking is found during 
the inspections required by paragraph (e) of this AD, repeat the 
inspections on the upper and lower outboard flange at the firewall 
within the applicable intervals specified in paragraph 1.E., Table 
1, of Boeing Service Bulletin 727-54A0010, Revision 6, dated August 
23, 2001.
    (1) Repeat the inspections of the upper outboard flange at the 
firewall until the modification required by paragraph (j) of this AD 
has been done.
    (2) Repeat the inspections of the lower outboard flange at the 
firewall indefinitely. There is no terminating action for the 
inspections of this area.

    Note 5: Boeing Service Bulletin 727-54A0010, Revision 6, dated 
August 23, 2001, does not provide instructions for modifying the 
fastener holes of the lower outboard flange at the firewall.

Cracking Found: Any Airplane

    (h) For any airplane: If any crack is found during any 
inspection required by paragraph (d), (e), (f), or (g) of this AD, 
before further flight, do the actions specified in either paragraph 
(h)(1) or (h)(2) of this AD.
    (1) Replace or repair the fitting in accordance with a method 
approved by the Manager, Seattle ACO; or according to data meeting 
the certification basis of the airplane approved by an Authorized 
Representative for the Boeing Delegation Option Authorization (DOA) 
Organization who has been authorized by the Manager, Seattle ACO, to 
make those findings. For a repair method to be approved, the repair 
must meet the certification basis of the airplane, and the approval 
must specifically refer to this AD; or
    (2) Do the modification specified in paragraph (j) of this AD.

Web Thickness Less Than 0.130 Inch: Any Airplane

    (i) For any airplane: If the web thickness measured during 
accomplishment of paragraph (d)(4) of this AD is less than 0.130 
inch, before further flight, replace or repair the fitting in 
accordance with a method approved by the Manager, Seattle ACO; or 
according to data meeting the certification basis of the airplane 
approved by an Authorized Representative for the Boeing DOA 
Organization who has been authorized by the Manager, Seattle ACO, to 
make those findings. For a repair method to be approved, the repair 
must meet the certification basis of the airplane, and the approval 
must specifically refer to this AD.

Modification

    (j) Except as required by paragraphs (h), (i), and (q) of this 
AD: Within 3,000 flight cycles or 24 months after the effective date 
of this AD, whichever occurs first, modify the fastener holes, in 
accordance with Part II of the Accomplishment Instructions of Boeing 
Service Bulletin 727-54A0010, Revision 6, dated August 23, 2001. 
Accomplishment of the modification terminates the repetitive 
inspections required by paragraphs (f) and (g)(1) of this AD.

Modification in Accordance With Prior Service Bulletin Revision

    (k) For airplanes modified before the effective date of this AD 
in accordance with Boeing Service Bulletin 727-54A0010, Revision 4, 
dated January 30, 1997: Paragraph (j) of this AD requires 
accomplishment of additional procedures in accordance with Revision 
6 of the service bulletin. To the extent that certain modification 
procedures were performed in accordance with Revision 4, those 
actions do not need to be repeated when performing the modification 
required in paragraph (j) of this AD.
    (l) A modification done before the effective date of this AD in 
accordance with Boeing Alert Service Bulletin 727-54A0010, Revision 
5, dated February 15, 2001, is acceptable for compliance with the 
requirements of paragraph (j) of this AD.

Post-Modification Inspections

    (m) Inspect as specified in paragraphs (m)(1), (m)(2), and (n) 
of this AD, as applicable, to detect cracking and corrosion, in 
accordance with Part III of the Accomplishment Instructions of 
Boeing Service Bulletin 727-54A0010, Revision 6, dated August 23, 
2001. Inspections done before the effective date of this AD in 
accordance with Part III of Boeing Alert Service Bulletin 727-
54A0010, Revision 5, dated February 15, 2001, are acceptable for 
compliance with the corresponding inspection requirements of this 
paragraph.
    (1) For all airplanes: Do an open hole HFEC inspection of the 
fastener holes in the forward support fitting of the number 1 and 
number 3 engines, at the locations shown in Figure 4 of the service 
bulletin.
    (2) For Group 2 airplanes: Do an open hole HFEC inspection of 
the fastener holes in the forward support fitting of the number 1 
and number 3 engines, at the locations shown in Figure 4 of the 
service bulletin.
    (n) Perform the inspections specified in paragraph (m) of this 
AD at the later of the times specified in paragraphs (n)(1) and 
(n)(2) of this AD.
    (1) Within 3,000 flight cycles or 24 months, whichever occurs 
first, after accomplishment of the modification required by 
paragraph (j) of this AD.
    (2) Within 600 flight cycles or 100 days, whichever occurs 
first, after the effective date of this AD.

Follow-On/Corrective Actions

    (o) If no cracking is found during any inspection required by 
paragraph (m) of this AD: Repeat the inspections specified in 
paragraph (m) of this AD thereafter within the applicable intervals 
specified in paragraph 1.E., Table 1, of Boeing Service Bulletin 
727-54A0010, Revision 6, dated August 23, 2001. Accomplishment of 
the modification specified in paragraph (j) of this AD does not 
terminate the requirement to repetitively perform the post-
modification inspections specified in Part III of the service 
bulletin.
    (p) If any cracking is detected during any inspection required 
by paragraph (m) of this AD: Before further flight, repair in 
accordance with Boeing Service Bulletin 727-54A0010, Revision 6, 
dated August 23, 2001; except as required by paragraph (q) of this 
AD.

Exception to Corrective Actions

    (q) Where Boeing Service Bulletin 727-54A0010, Revision 6, dated 
August 23, 2001, specifies to contact Boeing for appropriate action: 
Before further flight, replace or repair the fitting in accordance 
with a method approved by the Manager, Seattle ACO; or according to 
data meeting the certification basis of the airplane approved by an 
Authorized Representative for the Boeing DOA Organization who has 
been authorized by the Manager, Seattle ACO, to make those findings. 
For a repair method to be approved, the repair must meet the 
certification basis of the airplane, and the approval must 
specifically refer to this AD.

Reporting Not Required

    (r) Boeing Service Bulletin 727-54A0010, Revision 6, dated 
August 23, 2001, recommends that operators report inspection results 
to the manufacturer; however, this AD does not contain this 
requirement.

Parts Installation

    (s) As of the effective date of this AD, no person may install a 
forward support fitting on any airplane, unless it has been 
inspected and modified, as applicable, in accordance with the 
requirements of this AD.

Alternative Methods of Compliance

    (t)(1) The Manager, Seattle ACO, FAA, has the authority to 
approve AMOCs for this AD, if requested in accordance with the 
procedures found in 14 CFR 39.19.
    (2) AMOCs previously approved according to AD 97-05-08 are 
acceptable for

[[Page 55529]]

compliance with the corresponding requirements of this AD.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing DOA Organization who has 
been authorized by the Manager, Seattle ACO, to make those findings. 
For a repair method to be approved, the repair must meet the 
certification basis of the airplane, and the approval must 
specifically refer to this AD.

    Note 6: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permits

    (u) Special flight permits may be issued according to 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.

Incorporation by Reference

    (v) Unless otherwise specified in this AD, the actions must be 
done in accordance with Boeing Service Bulletin 727-54A0010, 
Revision 4, dated January 30, 1997; and Boeing Service Bulletin 727-
54A0010, Revision 6, including Appendix A, dated August 23, 2001; as 
applicable.
    (1) The incorporation by reference of Boeing Service Bulletin 
727-54A0010, Revision 6, including Appendix A, dated August 23, 
2001, is approved by the Director of the Federal Register in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) The incorporation by reference of Boeing Service Bulletin 
727-54A0010, Revision 4, dated January 30, 1997, was approved 
previously by the Director of the Federal Register as of March 18, 
1997 (62 FR 9359, March 3, 1997).
    (3) 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 the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

Effective Date

    (w) This amendment becomes effective on October 27, 2005.

    Issued in Renton, Washington, on September 8, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-18783 Filed 9-21-05; 8:45 am]
BILLING CODE 4910-13-P