Federal Register / Vol. 70, No. 131 / Monday, July 11, 2005 / Rules and Regulations 39647

FR 34094, June 27, 2001), are approved as 

AMOCs for the inspection requirements of 

this AD only at fastener locations where the 

AMOC provided for installing either 

BACB30NX or BACB30US fasteners. 

Material Incorporated by Reference 

(q) You must use Boeing Alert Service 

Bulletin 747–57A2312, dated June 15, 2000; 

or Boeing Alert Service Bulletin 747–

57A2312, Revision 1, dated April 29, 2004; 

to perform the actions that are required by 

this AD, unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approves the incorporation by reference of 

Boeing Alert Service Bulletin 747–57A2312, 

Revision 1, dated April 29, 2004, in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of Boeing Alert Service Bulletin 

747–57A2312, dated June 15, 2000, as of 

August 1, 2001 (66 FR 34094, June 27, 2001). 

(3) 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.

Issued in Renton, Washington, on June 29, 

2005. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 05–13432 Filed 7–8–05; 8:45 am] 

BILLING CODE 4910–13–P

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.

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 noncompliance’’ 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 

39648 Federal Register / Vol. 70, No. 131 / Monday, July 11, 2005 / Rules and Regulations 

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 carriage attach fittings 4 None ....................... $222,300, or $260 per airplane, per inspection cycle. 

Certain airplanes .... Installation of guide blocks ...................... 32 Free ........................ $2,080 per airplane. 

Certain airplanes .... Inspection of foreflap airload roller travel 4 None ....................... $260 per airplane. 

Certain airplanes .... Modification of the inboard jackscrews 

on the outboard flap.

4 Free ........................ $260 per airplane. 

Certain airplanes .... Inspection of the entire track and of the 

track rib faces.

12 None ....................... $780 per airplane. 

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 

Federal Register / Vol. 70, No. 131 / Monday, July 11, 2005 / Rules and Regulations 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

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows:

PART 39—AIRWORTHINESS 

DIRECTIVES

■ 1. The authority citation for part 39 

continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

■ 2. The FAA amends § 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. 

39650 Federal Register / Vol. 70, No. 131 / Monday, July 11, 2005 / Rules and Regulations 

(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:

Page number Revision level 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:

Federal Register / Vol. 70, No. 131 / Monday, July 11, 2005 / Rules and Regulations 39651

Page number Revision level 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 727–57A0135 ............................................... 3 June 27, 2002. 

Boeing Service Bulletin 727–27–133 .......................................................... 1 May 9, 1972. 

Boeing 727 Service Bulletin 57–59 ............................................................. 1 September 27, 1965. 

Boeing 727 Service Bulletin 57–72 ............................................................. Original September 21, 1966. 

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21463; Directorate 

Identifier 2005–CE–30–AD; Amendment 39–

14144; AD 2005–12–51] 

RIN 2120–AA64 

Airworthiness Directives; Rockwell 

International (Aircraft Specification No. 

A–2–575 Previously Held by North 

American and Recently Purchased by 

Boeing) Models AT–6 (SNJ–2), AT–6A 

(SNJ–3), AT–6B, AT–6C (SNJ–4), AT–

6D (SNJ–5), AT–6F (SNJ–6), BC–1A, 

SNJ–7, and T–6G Airplanes; and Autair 

Ltd. (Aircraft Specification No. AR–11 

Previously Held by Noorduyn Aviation 

Ltd.) Model Harvard (Army AT–16) 

Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule; correction

SUMMARY: This document makes a 

correction to Airworthiness Directive 

(AD) 2005–12–51, which was published 

in the Federal Register on June 21, 2005 

(70 FR 35519), and applies to Rockwell 

International (Aircraft Specification No. 

A–2–575 previously held by North 

American and recently purchased by 

Boeing) Models AT–6 (SNJ–2), AT–6A 

(SNJ–3), AT–6B, AT–6C (SNJ–4), AT–6D 

(SNJ–5), AT–6F (SNJ–6), BC–1A, SNJ–7, 

and T–6G airplanes; and Autair Ltd. 

(Aircraft Specification No. AR–11 

previously held by Noorduyn Aviation 

Ltd.) Model Harvard (Army AT–16) 

airplanes. We incorrectly referenced the 

docket number as FAA–2005–24163 

throughout the document. The correct 

docket number is FAA–2005–21463. 

This action corrects the regulatory text.

DATES: The effective date of this AD 

remains June 23, 2005.

FOR FURTHER INFORMATION CONTACT: Fred 

Guerin, Aerospace Engineer, FAA, Los 

Angeles ACO, 3960 Paramount Blvd., 

Lakewood, CA 90712; telephone: (562) 

627–5232; facsimile: (562) 627–5210; email: fred.guerin@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion 

On June 14, 2005, FAA issued AD 

2005–12–51, Amendment 39–14144 (70 

FR 35519, June 21, 2005), which applies 

to Rockwell International (Aircraft 

Specification No. A–2–575 previously 

held by North American and recently 

purchased by Boeing) Models AT–6 

(SNJ–2), AT–6A (SNJ–3), AT–6B, AT–

6C (SNJ–4), AT–6D (SNJ–5), AT–6F 

(SNJ–6), BC–1A, SNJ–7, and T–6G 

airplanes; and Autair Ltd. (Aircraft 

Specification No. AR–11 previously 

held by Noorduyn Aviation Ltd.) Model 

Harvard (Army AT–16) airplanes. 

We incorrectly referenced the docket 

number as FAA–2005–24163 

throughout the document. The correct 

docket number is FAA–2005–21463. 

This action corrects the regulatory text. 

This AD requires immediate and 

repetitive inspections of the inboard and 

outboard, upper and lower wing attach 

angles (except for the nose angles) of 

both wings for fatigue cracks; and, if any 

crack is found, replacement of the 

cracked angle with a new angle. 

Need for the Correction 

This correction is needed to ensure 

that any comments (any written relevant 

data, views, or arguments regarding this 

AD) made by the public are 

appropriately filed and to eliminate 

misunderstanding in the field. 

Correction of Publication

■ Accordingly, the publication of June 

21, 2005 (70 FR 35519), of Amendment 

39–14144; AD 2005–12–51, which was 

the subject of FR Doc. 05–12151, is 

corrected as follows:

■ Starting on page 35519 through page 

35523, replace all references to Docket 

No. FAA–2005–24163 with Docket No. 

FAA–2005–21463.

PART 39—[AMENDED]

§ 39.13 [Corrected]

■ On page 35521, in section 39.13 

[Amended], in paragraph 2, replace 

Docket No. FAA–2005–24163 with 

Docket No. FAA–2005–21463.

■ On page 35523, in section 39.13 

[Amended], in paragraph (h), replace 

Docket No. FAA–2005–24163 with 

Docket No. FAA–2005–21463. 

The effective date remains June 23, 

2005.