58000 Federal Register / Vol. 70, No. 192 / Wednesday, October 5, 2005 / Rules and Regulations 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding an airworthiness directive 

(AD) that removes amendment 39–7031 

(56 FR 26610, June 10, 1991), to read as 

follows: 

2005–20–31 Honeywell: Amendment 39–

14328. Docket No. FAA–2005–22585; 

Directorate Identifier 2005–NM–041–AD. 

Rescinds AD 91–08–51, Amendment 39–

7031. 

Effective Date 

(a) This AD becomes effective October 5, 

2005. 

Affected ADs 

(b) This action rescinds AD 91–08–51. 

Applicability 

(c) This action applies to Honeywell Flight 

Management System (FMS) one million word 

(1M or 700K) data bases (9104 cycle or 

earlier), as installed in, but not limited to, 

McDonnell Douglas Model MD–11 and MD–

11F airplanes, and Boeing Model 747–400 

series airplanes, Model 757–200, –200PF, 

–200CB, and –300 series airplanes, and 

Model 767–200, –300, –300F, and –400ER 

series airplanes, certificated in any category. 

Issued in Renton, Washington, on 

September 26, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19938 Filed 10–4–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22584; Directorate 

Identifier 2005–NM–044–AD; Amendment 

39–14313; AD 2004–19–06 R1] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 767–200, –300, and –300F Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is revising an 

existing airworthiness directive (AD) 

that applies to all Boeing Model 767–

200, –300, and –300F series airplanes. 

The existing AD currently requires 

inspections to detect cracking or 

corrosion of the fail-safe straps between 

the side fitting of the rear spar bulkhead 

at body station 955 and the skin; and 

follow-on/corrective actions. The 

existing AD results from reports of 

cracked and/or corroded fail-safe straps 

at body station (BS) 955 on Boeing 

Model 767–200 series airplanes. We 

issued the existing AD to detect and 

correct fatigue cracking or corrosion of 

the fail-safe straps, which could result 

in cracking of adjacent structure and 

consequent reduced structural integrity 

of the fuselage. This new AD revises the 

applicability of the existing AD to 

reduce the number of affected airplanes. 

We are issuing this AD to detect and 

correct fatigue cracking or corrosion of 

the fail-safe straps, which could result 

in cracking of adjacent structure and 

consequent reduced structural integrity 

of the fuselage. 

DATES: The effective date of this AD is 

November 1, 2004. 

On November 1, 2004 (69 FR 57636, 

September 27, 2004), the Director of the 

Federal Register approved the 

incorporation by reference of Boeing 

Alert Service Bulletin 767–53A0100, 

dated September 26, 2002. 

We must receive comments on this 

AD by December 5, 2005. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-Wide Rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street SW., Nassif Building, 

Room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

Contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Candice Gerretsen, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6428; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On September 13, 2004, we issued AD 

2004–19–06, amendment 39–13800 (69 

FR 57636, September 27, 2004). That 

AD applies to all Boeing Model 767–

200, –300, and –300F series airplanes. 

That AD requires inspections to detect 

cracking or corrosion of the fail-safe 

straps between the side fitting of the 

rear spar bulkhead at body station (BS) 

955 and the skin; and follow-on/ 

corrective actions. That AD resulted 

from reports of cracked and/or corroded 

fail-safe straps at BS 955 on Boeing 

Model 767–200 series airplanes. The 

actions specified in that AD are 

intended to detect and correct fatigue 

cracking or corrosion of the fail-safe 

straps, which could result in cracking of 

adjacent structure and consequent 

reduced structural integrity of the 

fuselage. 

Actions Since AD Was Issued 

Since we issued that AD, the 

manufacturer, Boeing, developed a 

production change that lowers the 

maximum stress in the fail-safe strap 

and removes the critical location where 

cracks were occurring on Boeing Model 

767–200, –300, and –300F series 

airplanes. The production change is 

applicable to airplanes having line 

numbers 932 and subsequent. Therefore, 

we have revised the applicability of AD 

2004–19–06 to Boeing Model 767–200, 

–300, and –300F series airplanes, line 

numbers 1 through 931 inclusive. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other airplanes of the same type 

design that may be registered in the U.S. 

at some time in the future. For this 

reason, we are issuing this AD to detect 

and correct fatigue cracking or corrosion 

of the fail-safe straps, which could 

result in cracking of adjacent structure 

and consequent reduced structural 

integrity of the fuselage. This AD 

continues to require inspections to 

detect cracking or corrosion of the failsafe straps between the side fitting of 

the rear spar bulkhead at body station 

955 and the skin; and follow-on/ 

corrective actions. This AD also revises 

the applicability of the existing AD to 

exclude line numbers 932 and 

subsequent. 

Explanation of Change Made to This 

AD 

Boeing Commercial Airplanes has 

received a Delegation Option 

Authorization (DOA). We have revised 

this AD to delegate the authority to 

approve an alternative method of 

Federal Register / Vol. 70, No. 192 / Wednesday, October 5, 2005 / Rules and Regulations 58001 

compliance for any repair required by 

this AD to an Authorized Representative 

for the Boeing Commercial Airplanes 

DOA rather than a Designated 

Engineering Representative (DER). 

Clarification of Alternative Method of 

Compliance (AMOC) Paragraph 

We have revised this AD to clarify the 

appropriate procedure for notifying the 

principal inspector before using any 

approved AMOC on any airplane to 

which the AMOC applies. 

Interim Action 

This is considered to be interim 

action until final action is identified, at 

which time we may consider further 

rulemaking. 

Costs of Compliance 

There are approximately 833 

airplanes of the affected design in the 

worldwide fleet. We estimate that 354 

airplanes of U.S. registry will be affected 

by this AD, that it will take 

approximately 2 work hours per 

airplane to accomplish the required 

inspections, and that the average labor 

rate is $65 per work hour. Based on 

these figures, the cost impact of the AD 

on U.S. operators is estimated to be 

$46,020, or $130 per airplane, per 

inspection cycle. 

FAA’s Determination of the Effective 

Date 

On April 18, 2005, the Seattle Aircraft 

Certification Office granted an 

alternative method of compliance 

(AMOC) with the requirements of AD 

2004–19–06 for airplanes having line 

numbers 932 and subsequent. That 

AMOC terminates the requirements of 

AD 2004–19–06 for those airplanes. 

This AD clarifies that the applicability 

of AD 2004–19–06 is only for airplanes 

having line numbers 1 through 931 

inclusive. Therefore, providing notice 

and opportunity for public comment is 

unnecessary before this AD is issued, 

and this AD may be made effective in 

less than 30 days after it is published in 

the Federal Register. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

relevant written data, views, or 

arguments regarding this AD. Send your 

comments to the address listed under 

the ADDRESSES section. Include ‘‘Docket 

No. FAA–2005–22584; Directorate 

Identifier 2005–NM–044–AD’’ at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the AD that might suggest a need to 

modify it. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of that web site, anyone 

can find and read the comments in any 

of our dockets, including the name of 

the individual who sent the comment 

(or signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78), or you may visit 

http://dms.dot.gov. 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Management 

Facility office between 9:00 a.m. and 

5:00 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 DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System receives them. 

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 

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 and placed it in the AD docket. 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–13800 (69 

FR 57636, September 27, 2004) and 

adding the following new airworthiness 

directive (AD): 

2004–19–06 R1 Boeing: Amendment 39–

14313. Docket No. FAA–2005–22584; 

Directorate Identifier 2005–NM–044–AD. 

Effective Date 

(a) The effective date of this AD is 

November 1, 2004. 

Affected ADs 

(b) This AD revises AD 2004–19–06. 

Applicability 

(c) This AD applies to Boeing Model 767–

200, –300, and –300F series airplanes, 

certificated in any category; line numbers 1 

through 931 inclusive. 

Unsafe Condition 

(d) This AD results from reports of cracked 

and/or corroded fail-safe straps at body 

station (BS) 955 on Boeing Model 767–200 

series airplanes. We are issuing this AD to 

detect and correct fatigue cracking or 

corrosion of the fail-safe straps, which could 

58002 Federal Register / Vol. 70, No. 192 / Wednesday, October 5, 2005 / Rules and Regulations 

result in cracking of adjacent structure and 

consequent reduced structural integrity of the 

fuselage. 

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 and Follow-On/Corrective 

Actions 

(f) Except as provided by paragraph (g) of 

this AD, prior to the accumulation of 15,000 

total flight cycles, or within 3,000 flight 

cycles after November 1, 2004 (the effective 

date of AD 2004–19–06), whichever occurs 

later, perform a detailed inspection and eddy 

current inspection to detect cracking or 

corrosion of the fail-safe straps between the 

side fitting of the rear spar bulkhead at BS 

955 and the skin, per Figure 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–53A0100, dated 

September 26, 2002. 

Note 1: 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.’’

(1) If no crack or corrosion is found, repeat 

the inspections thereafter at intervals not to 

exceed 6,000 flight cycles or 36 months, 

whichever occurs first. 

(2) If any crack or corrosion is found, 

before further flight, repair per a method 

approved by the Manager, Seattle Aircraft 

Certification Office (ACO), FAA; or using a 

method approved in accordance with 

paragraph (h)(2) of this AD. 

(g) For airplanes on which the fail-safe 

strap has been replaced before November 1, 

2004: Do the actions required by paragraph 

(f) of this AD within 12,000 flight cycles after 

accomplishing the replacement. 

Note 2: Steps 2 and 8 of the Work 

Instructions of Boeing Alert Service Bulletin 

767–53A0100, dated September 26, 2002, 

refer incorrectly to 767 Airplane 

Maintenance Manual (AMM) 32–00–20 for 

opening the MLG doors; the correct reference 

is 767 AMM 32–00–15, which is referred to 

in steps 3 and 7 of the Work Instructions. 

Step 2 also should state ‘‘Open Main Landing 

Gear (MLG) doors’’ instead of ‘‘Open Main 

Landing Green (MLG) doors.’’

Alternative Methods of Compliance 

(AMOCs) 

(h)(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) Before using any AMOC approved in 

accordance with 14 CFR 39.19 on any 

airplane to which the AMOC applies, notify 

the appropriate principal inspector in the 

FAA Flight Standards Certificate Holding 

District Office. 

(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 

Commercial Airplanes Delegation Option 

Authorization 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. 

Material Incorporated by Reference 

(i) You must use Boeing Alert Service 

Bulletin 767–53A0100, dated September 26, 

2002, to perform the actions that are required 

by this AD, unless the AD specifies 

otherwise. On November 1, 2004 (69 FR 

57636, September 27, 2004), the Director of 

the Federal Register approved the 

incorporation by reference of this document. 

Contact Boeing Commercial Airplanes, P.O. 

Box 3707, Seattle, Washington 98124–2207, 

for a copy of this service information. You 

may review copies at the Docket Management 

Facility, U.S. Department of Transportation, 

400 Seventh Street SW., room PL–401, Nassif 

Building, Washington, DC; on the Internet at 

http://dms.dot.gov; 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. 

Issued in Renton, Washington, on 

September 26, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19939 Filed 10–4–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21085; Directorate 

Identifier 2004–NM–252–AD; Amendment 

39–14307; AD 2005–20–13] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 727 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Boeing Model 727 airplanes. This AD 

requires a one-time inspection of the 

lower lobe frames of body section 43 to 

find open holes between stringers 17L 

and 17R and to record their location; 

repetitive high frequency eddy current 

(HFEC) inspections for cracks of all 

open holes; and related investigative 

and corrective actions if necessary. This 

AD also includes an optional 

terminating action of installing rivets in 

all open tooling holes and all unused 

lining holes, which would terminate the 

repetitive open-hole HFEC inspections 

once a hole is plugged with a rivet. This 

AD results from reports of cracks at 

open tooling holes in the lower lobe 

frames of body section 43. We are 

issuing this AD to detect and correct 

cracks in the frames, which could result 

in cracks in the skin panels and rapid 

decompression of the airplane. 

DATES: This AD becomes effective 

November 9, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 9, 2005. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street 

SW., Nassif Building, room PL–401, 

Washington, DC. 

Contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for service 

information identified in this 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: 

Examining the Docket 

You may examine the airworthiness 

directive (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 street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to all Boeing Model 727 airplanes. 

That NPRM was published in the 

Federal Register on May 2, 2005 (70 FR 

22618). That NPRM proposed to require 

a one-time inspection of the lower lobe 

frames of body section 43 to find open 

holes between stringers 17L and 17R 

and to record their location; repetitive 

high frequency eddy current (HFEC) 

inspections for cracks of all open holes; 

and related investigative and corrective 

actions if necessary. That NPRM also