[Federal Register Volume 70, Number 131 (Monday, July 11, 2005)]
[Rules and Regulations]
[Pages 39647-39651]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-13434]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19679; Directorate Identifier 2003-NM-132-AD; 
Amendment 39-14184; AD 2005-14-07]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727, 727C, 727-100, 727-
100C, 727-200, and 727-200F Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Boeing Model 727, 727C, 727-100, 727-100C, 727-200, and 727-
200F series airplanes. This AD requires repetitive inspections of the 
carriage attach fittings on the foreflaps of each wing for cracking and 
other discrepancies, and corrective actions if necessary. For certain 
airplanes, this AD also concurrently requires various other actions 
related to the subject area. This AD also provides for an optional 
terminating action for the repetitive inspection requirements and for 
an optional replacement that defers the repetitive inspections. This AD 
is prompted by reports of damaged or failed outboard foreflaps with a 
cracked or failed carriage attach fitting of the foreflap sequencing 
carriage. We are issuing this AD to detect and correct fatigue cracking 
of the attach fittings of the foreflap carriage of the wings, which 
could result in partial or complete loss of the foreflap and consequent 
loss of controllability of the airplane.

DATES: This AD becomes effective August 15, 2005.
    The incorporation by reference of certain publications listed in 
the AD is approved by the Director of the Federal Register as of August 
15, 2005.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
    Docket: The AD docket contains the proposed AD, comments, and any 
final disposition. You can examine the AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility 
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the U.S. 
Department of Transportation, 400 Seventh Street, SW., room PL-401, 
Washington, DC. This docket number is FAA-2004-19679; the directorate 
identifier for this docket is 2003-NM-132-AD.

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: The FAA proposed to amend 14 CFR part 39 
with an AD for certain Boeing Model 727, 727C, 727-100, 727-100C, 727-
200, and 727-200F series airplanes. That action, published in the 
Federal Register on November 24, 2004 (69 FR 68274), proposed to 
require repetitive inspections of the carriage attach fittings on the 
foreflaps of each wing for cracking and other discrepancies, and 
corrective actions if necessary. For certain airplanes, that action 
also proposed to concurrently require various other actions related to 
the subject area. That action also proposed an optional terminating 
action for the repetitive inspection requirements and an optional 
replacement that defers the repetitive inspections.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
submitted on the proposed AD.

Support for Proposed AD

    One commenter, the airplane manufacturer, supports the proposed AD.

Request To Revise Applicability

    One commenter requests that the applicability of the proposed AD 
refer to serial numbers (S/N) of the foreflap assembly rather than to 
the S/Ns of the affected airplanes. The commenter states that flight 
controls are often swapped from airplane to airplane to accommodate 
maintenance and overhaul requirements. The commenter believes that 
tracking the S/N of the foreflap assembly will ensure that all affected 
parts (including spares) are modified, reworked, or replaced.
    We do not agree. The foreflap assembly is part of the type design 
for the affected Model 727 airplanes. Our general policy is that, when 
an unsafe condition has been identified, the AD is issued so that it is 
applicable to the type-certificated airplane, not to an item that is 
part of the type design. Making the AD applicable to the airplane model 
ensures that operators of those airplanes will be notified directly of 
the unsafe condition and the action required to correct it. While it is 
assumed that an operator will know the models of airplanes that it 
operates, there is a potential that the operator will not know or be 
aware of specific items, such as a foreflap assembly, that are 
installed on its airplanes. Therefore, calling out the airplane model 
as the subject of the AD prevents ``unknowing non-compliance'' on the 
part of the operator. We have made no change in this regard to the AD.

Request To Extend Compliance Time

    One commenter requests that the compliance time specified in 
paragraph (h) of the proposed AD be revised from 3,500 flight cycles to 
4,500 flight cycles. The commenter states that the modification 
instructions in paragraph G. of Part II of the Accomplishment

[[Page 39648]]

Instructions of Boeing Service Bulletin 727-27-133, Revision 1, dated 
May 9, 1972 (referred to in paragraph (k) of the proposed AD as the 
appropriate source of service information for accomplishing concurrent 
requirements) involve part replacement, and in order to maintain a C-
check schedule, a retrofit program must be put in place. This retrofit 
program would be costly and time consuming.
    We do not agree. The commenter provides no technical justification 
for extending the compliance time for the inspection required by 
paragraph (h) of the AD. In developing an appropriate compliance time, 
we considered the safety issues as well as the recommendations of the 
airplane manufacturer, and the practical aspect of accomplishing the 
required actions within a period of time that corresponds to the normal 
scheduled maintenance for most affected operators. In light of these 
items, we have determined that the compliance time of within 3,500 
flight cycles after the effective date of this AD in paragraph (h) of 
this AD is appropriate. However, paragraph (r) of this AD provides 
affected operators the opportunity to apply for an adjustment of the 
compliance time if the operator also presents data that justify the 
adjustment.

Request To Revise Service Bulletin

    One commenter requests that Boeing Service Bulletin 727-27-133, 
Revision 1, dated May 9, 1972, be revised to include figures 
illustrating all dimensions to ensure accuracy and consistency with 
existing airplane maintenance manual (AMM) procedures. The commenter 
notes that in paragraph A.1. of Part I of the Accomplishment 
Instructions of the service bulletin, Chapter 27-51-0 of the AMM is 
specified as the source of service information for the ``X dimension.'' 
The commenter states that the AMM lists the dimension as ``X2-X1,'' but 
not as ``X dimension.'' The commenter further states that there is no 
Boeing master AMM, and each operator's AMM is a little different from 
the other operators' AMMs; therefore, consistency has a big part to 
play in carrying out the service bulletin instructions.
    We do not agree. Chapter 27-51-0 of the AMM does illustrate ``X 
dimension'' in multiple locations (figures and tables). It also defines 
``X1 dimension'' as ``X dimension'' for flaps in the up position and 
``X2 dimension'' as ``X dimension'' for each flap position other than 
flaps up. We find no change is necessary to the AD in this regard.
    The same commenter also requests that Figure 1 of Boeing Service 
Bulletin 727-27-133 show the airload support roller in relation to the 
foreflap track for clarity purposes. The commenter states that 
illustrating the airload support roller with the track will help 
operators to better visualize the area while accomplishing paragraph H. 
of Part I of the Accomplishment Instructions of the service bulletin.
    We do not agree. Although additional details in Figure 1 would be 
helpful to operators, the service bulletin contains the necessary 
information for accomplishing the required actions. In addition, Boeing 
Alert Service Bulletin 727-57A0135, Revision 3, dated June 27, 2002, 
which is also referenced in this AD as an appropriate source of service 
information, shows the location of the airload support rollers. 
Therefore, we have made no change to the AD in this regard.

Changes to Delegation Authority

    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 (AR) for the Boeing DOA Organization 
rather than the Designated Engineering Representative (DER).
    In addition, we inadvertently omitted from paragraph (k)(1)(ii) of 
the proposed AD the following sentence: ``For a repair method to be 
approved, the repair must meet the certification basis of the airplane, 
and the approval must specifically reference this AD.'' This language 
was included elsewhere in the proposed AD for accomplishing certain 
conditions in one of the following ways:
     Using a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by an AR for the Boeing DOA 
Organization who has been authorized by the FAA to make those findings. 
Therefore, we have revised paragraph (k)(1)(ii) of the AD accordingly.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been submitted, and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We have determined that these changes will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    There are about 1,292 airplanes of the affected design in the 
worldwide fleet. We estimate that 855 airplanes of U.S. registry will 
be affected by this AD. The average labor rate is $65 per work hour. 
The following table provides the estimated costs for U.S. operators to 
comply with this AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
              For--                       Action          Work hours       Parts cost               Cost
----------------------------------------------------------------------------------------------------------------
All airplanes....................  Inspections of the              4  None................  $222,300, or $260
                                    carriage attach                                          per airplane, per
                                    fittings.                                                inspection cycle.
Certain airplanes................  Installation of                32  Free................  $2,080 per airplane.
                                    guide blocks.
Certain airplanes................  Inspection of                   4  None................  $260 per airplane.
                                    foreflap airload
                                    roller travel.
Certain airplanes................  Modification of the             4  Free................  $260 per airplane.
                                    inboard jackscrews
                                    on the outboard
                                    flap.
Certain airplanes................  Inspection of the              12  None................  $780 per airplane.
                                    entire track and of
                                    the track rib faces.
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Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for

[[Page 39649]]

safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD 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.
    For the reasons discussed above, I certify that this AD:
    (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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD. See the ADDRESSES section for a location to 
examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 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. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2005-14-07 Boeing: Amendment 39-14184. Docket No. FAA-2004-19679; 
Directorate Identifier 2003-NM-132-AD.

Effective Date

    (a) This AD becomes effective August 15, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 727, 727C, 727-100, 727-
100C, 727-200, and 727-200F series airplanes, as listed in Boeing 
Alert Service Bulletin 727-57A0135, Revision 3, dated June 27, 2002; 
certificated in any category.

Unsafe Condition

    (d) This AD was prompted by reports of damaged or failed 
outboard foreflaps with a cracked or failed carriage attach fitting 
of the foreflap sequencing carriage. We are issuing this AD to 
detect and correct fatigue cracking of the attach fittings of the 
foreflap carriage of the wings, which could result in partial or 
complete loss of the foreflap and consequent loss of controllability 
of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Inspections

    (f) Except as provided by paragraph (o) of this AD: Within 1,000 
flight cycles after the effective date of this AD, and thereafter at 
intervals not to exceed 1,000 flight cycles, inspect as specified in 
paragraphs (f)(1) and (f)(2) of Table 1 of this AD in accordance 
with the Accomplishment Instructions of Boeing Alert Service 
Bulletin 727-57A0135, Revision 3, dated June 27, 2002. Table 1 is as 
follows:

                    Table 1.--Inspection Requirements
------------------------------------------------------------------------
        Requirements--                       Description--
------------------------------------------------------------------------
(1) Area to inspect..........  The two carriage attach fittings on the
                                inboard and outboard foreflaps of each
                                wing.
(2) Type of inspections......  (i) A detailed inspection to detect
                                cracks and surface deviations on all
                                edges, surfaces, and lug attachment
                                fastener holes.
                               (ii) A high frequency eddy current (HFEC)
                                inspection to detect cracks at the lug
                                attachment fastener holes.
------------------------------------------------------------------------

Crack or Surface Deviation Findings: Replacement

    (g) If any crack is detected or if any surface deviation beyond 
the limits specified in the service bulletin is detected during any 
inspection required by paragraph (f) of this AD, before further 
flight, replace the carriage attach fitting with a new, improved 
fitting or a new fitting having the same part number as the existing 
fitting, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 727-57A0135, Revision 3, dated June 
27, 2002.

Measurement and Associated Corrective Action(s)

    (h) Within 3,500 flight cycles after the effective date of this 
AD, inspect for interference between the carriage attach fitting and 
the carriage lug fitting, and do other related investigative actions 
by accomplishing all the actions specified in paragraph 3.C. and 
Figure 2 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 727-57A0135, Revision 3, dated June 27, 2002. Do the 
actions in accordance with the service bulletin.
    (i) If any discrepancy is found during any action required by 
paragraph (h) of this AD, before further flight, accomplish 
applicable corrective action(s) (e.g., adding a shim or reworking 
the carriage attachment lug assembly) in accordance with paragraph 
3.C. and Figure 2 of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 727-57A0135, Revision 3, dated June 27, 2002. Where 
the service bulletin specifies to contact the manufacturer if rework 
of the improved fitting is required: Before further flight, rework 
in accordance with a method approved by the Manager, Seattle 
Aircraft Certification Office (ACO), FAA, or in accordance with data 
meeting the type certification basis of the airplane approved by an 
Authorized Representative (AR) for the Boeing Delegation Option 
Authorization (DOA) Organization who has been authorized by the FAA 
to make such findings. For a repair method to be approved, the 
repair must meet the certification basis of the airplane, and the 
approval must specifically reference this AD.

Concurrent Requirements

    (j) For Model 727 airplanes listed in Boeing 727 Service 
Bulletin 57-59, Revision 1, dated September 27, 1965: Before or at 
the same time with the requirements of paragraph (h) of this AD, 
install guide blocks and bushings in the midflap ribs in accordance 
with the Accomplishment Instructions of the service bulletin.
    (k) For Model 727 airplanes listed in Boeing Service Bulletin 
727-27-133, Revision 1, dated May 9, 1972: Before or at the same 
time with the requirements of paragraph (h) of this AD, do the 
actions specified in paragraphs (k)(1) and (k)(2) of this AD, as 
applicable.
    (1) For Groups I and II airplanes identified in the service 
bulletin: Do a one-time inspection of the airload support roller for 
travel on the foreflap track in accordance with Part I of the 
Accomplishment Instructions of the service bulletin.

[[Page 39650]]

    (i) If the airload support roller travels within the limits 
specified in the service bulletin, modify the control drum of the 
inboard flap and inboard jackscrews of the outboard flap, in 
accordance with Part II of the Accomplishment Instructions of the 
service bulletin.
    (ii) If the airload support roller travels beyond the limits 
specified in the service bulletin, repair in accordance with a 
method approved by the Manager, Seattle ACO, FAA; or in accordance 
with data meeting the type certification basis of the airplane 
approved by an AR for the Boeing DOA Organization who has been 
authorized by the FAA to make such findings. For a repair method to 
be approved, the repair must meet the certification basis of the 
airplane, and the approval must specifically reference this AD.
    (2) For Group III airplanes identified in the service bulletin: 
Modify the inboard jackscrews of the outboard flap (i.e., replacing 
the down stop at the inboard jackscrews of the outboard flap) in 
accordance with Part II of the Accomplishment Instructions of the 
service bulletin.
    (1) For Model 727 airplanes listed in Boeing 727 Service 
Bulletin 57-72, dated September 21, 1966: Before or at the same time 
with the requirements of paragraph (h) of this AD, do the actions 
specified in paragraphs (l)(1) through (l)(4) of this AD.
    (1) Chamfer the upper and lower flanges at the aft end of the 
foreflap tracks in accordance with the Accomplishment Instructions 
of the service bulletin.
    (2) Do a standard magnetic particle inspection of the entire 
foreflap tracks for cracks in accordance with the Accomplishment 
Instructions of the service bulletin. If any crack is detected, 
before further flight, repair in accordance with a method approved 
by the Manager, Seattle ACO, FAA; or in accordance with data meeting 
the type certification basis of the airplane approved by an AR for 
the Boeing DOA Organization who has been authorized by the FAA to 
make such findings. For a repair method to be approved, the repair 
must meet the certification basis of the airplane, and the approval 
must specifically reference this AD.
    (3) Do a general visual inspection of the track rib faces at the 
front and rear spars to verify if the opening in the spars is flush 
with or clear of the plane of the rib faces, in accordance with the 
Accomplishment Instructions of the service bulletin. If the opening 
is not flush or clear with the plane, before further flight, rework 
the spar opening in accordance with the Accomplishment Instructions 
of the service bulletin.
    (4) Do a general visual inspection of the head or shank of bolts 
by securing the foreflap links to the foreflap tracks to verify if 
they protrude beyond the edge of the track flange in accordance with 
the Accomplishment Instructions of the service bulletin. If the head 
or shank of the bolts protrude beyond the edge of the track flange, 
before further flight, rework in accordance with the Accomplishment 
Instructions of the service bulletin.

    Note 1: For the purposes of this AD, a general visual inspection 
is defined as: ``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 enhance visual access to all exposed 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.''

    (m) For airplanes other than those identified in the service 
bulletins specified in paragraphs (j) through (l) of this AD: Before 
or at the same time with the requirements of paragraph (h) of this 
AD, do an inspection to verify if any of the parts listed in the 
``Spares Affected'' paragraph of each service bulletin referenced in 
paragraphs (j) through (l) of this AD are installed on the airplane. 
If any part identified in that paragraph is found installed, before 
further flight, do the applicable corrective and investigative 
action(s) specified in paragraphs (j) through (1) of this AD.

Optional Terminating Actions

    (n) Replacement of the two carriage attach fittings on the 
inboard and outboard foreflaps of each wing with new, improved 
fittings, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 727-57A0135, Revision 3, dated June 
27, 2002; and accomplishment of the actions specified in paragraphs 
(j) through (m) of this AD, as applicable, before or concurrently 
with the replacement; constitutes terminating action for the 
requirements of this AD.

Optional Deferral of Inspection

    (o) Replacement of the two carriage attach fittings on the 
inboard and outboard foreflaps of each wing with new fittings having 
the same part number as the existing fittings, in accordance with 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
727-57A0135, Revision 3, dated June 27, 2002; and accomplishment of 
the actions specified in paragraphs (j) through (m) of this AD, as 
applicable, before or concurrently with the replacement; defers the 
next inspection required by paragraph (f) of this AD for 10,000 
flight cycles after the replacement. Thereafter, repeat the 
inspections required by paragraph (f) of this AD at intervals not to 
exceed 1,000 flight cycles.

Credit for Previously Accomplished Service Bulletins

    (p) Installations accomplished before the effective date of this 
AD in accordance with Boeing 727 Service Bulletin 57-59, dated 
September 2, 1965, are acceptable for compliance with the 
requirements of paragraph (j) of this AD.
    (q) Inspections and modifications accomplished before the 
effective date of this AD in accordance with Boeing Service Bulletin 
727-27-133, dated October 7, 1971, are acceptable for compliance 
with the requirements of paragraph (k) of this AD.

Alternative Methods of Compliance (AMOCs)

    (r)(1) In accordance with 14 CFR 39.19, the Manager, Seattle 
ACO, FAA, is authorized to approve alternative methods of compliance 
for this AD.
    (2) 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 AR 
for the Boeing DOA Organization who has been authorized by the FAA 
to make such findings. For a repair method to be approved, the 
repair must meet the certification basis of the airplane, and the 
approval must specifically reference this AD.

Material Incorporated by Reference

    (s) You must use the service bulletins identified in Table 2 of 
this AD to perform the actions that are required by this AD, unless 
the AD specifies otherwise. Boeing Service Bulletin 727-27-133, 
Revision 1, dated May 9, 1972, contains the following list of 
effective pages:

 
------------------------------------------------------------------------
                                    Revision level
           Page number               shown on page    Date shown on page
------------------------------------------------------------------------
1, 12, 14-18, 27................  1.................  May 9, 1972.
2-11, 13, 19-26, 28.............  Original..........  October 7, 1971.
------------------------------------------------------------------------

    Boeing 727 Service Bulletin 57-59, Revision 1, dated September 
27, 1965, contains the following list of effective pages:

[[Page 39651]]



 
------------------------------------------------------------------------
                                    Revision level
           Page number            date shown on page  Date shown on page
------------------------------------------------------------------------
1, 4, 6.........................  1.................  September 27,
                                                       1965.
2, 3, 5.........................  Original..........  September 2, 1965.
------------------------------------------------------------------------

    The Director of the Federal Register approves the incorporation 
by reference of these documents in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51. To get copies of the service information, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 
98124-2207. To view the AD docket, go to the Docket Management 
Facility, U.S. Department of Transportation, 400 Seventh Street, 
SW., room PL-401, Nassif Building, Washington, DC. To review copies 
of the service information, go to 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.

              Table 2.--Material Incorporated by Reference
------------------------------------------------------------------------
        Service bulletin            Revision level           Date
------------------------------------------------------------------------
Boeing Alert Service Bulletin                     3  June 27, 2002.
 727-57A0135.
Boeing Service Bulletin 727-27-                   1  May 9, 1972.
 133.
Boeing 727 Service Bulletin 57-                   1  September 27, 1965.
 59.
Boeing 727 Service Bulletin 57-            Original  September 21, 1966.
 72.
------------------------------------------------------------------------


    Issued in Renton, Washington, on June 29, 2005.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-13434 Filed 7-8-05; 8:45 am]
BILLING CODE 4910-13-P