Federal Register / Vol. 69, No. 89 / Friday, May 7, 2004 / Rules and Regulations 25481

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2004–NM–44–AD; Amendment 

39–13622; AD 2004–09–32] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 757–200 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) that is 

applicable to certain Boeing Model 757–

200 series airplanes. This action 

requires initial and repetitive 

inspections of the fuselage skin and bear 

strap at the forward, upper corner of the 

L1 entry door cutout for cracking, and 

repair if necessary. This action also 

provides an optional terminating action 

for the repetitive inspections. This 

action is necessary to detect and correct 

cracking of the fuselage skin and bear 

strap at the forward, upper corner of the 

L1 entry door cutout, which could result 

in reduced structural integrity of the L1 

entry door and consequent rapid 

decompression of the airplane. This 

action is intended to address the 

identified unsafe condition.

DATES: Effective May 24, 2004. 

The incorporation by reference of a 

certain publication listed in the 

regulations is approved by the Director 

of the Federal Register as of May 24, 

2004. 

Comments for inclusion in the Rules 

Docket must be received on or before 

July 6, 2004.

ADDRESSES: Submit comments in 

triplicate to the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, ANM–114, 

Attention: Rules Docket No. 2004–NM–

44–AD, 1601 Lind Avenue, SW., 

Renton, Washington 98055–4056. 

Comments may be inspected at this 

location between 9 a.m. and 3 p.m., 

Monday through Friday, except Federal 

holidays. Comments may be submitted 

via fax to (425) 227–1232. Comments 

may also be sent via the Internet using 

the following address: 9-anmiarcomment@faa.gov. Comments sent 

via fax or the Internet must contain 

‘‘Docket No. 2004–NM–44–AD’’ in the 

subject line and need not be submitted 

in triplicate. Comments sent via the 

Internet as attached electronic files must 

be formatted in Microsoft Word 97 or 

2000 or ASCII text. 

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 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue, SW., Renton, 

Washington; or at the National Archives 

and Records Administration (NARA). 

For information on the availability of 

this material at NARA, call (202) 741–

6030, or go to: http://www.archives.gov/

federal_register/

code_of_federal_regulations/

ibr_locations.html.

FOR FURTHER INFORMATION CONTACT:

Dennis Stremick, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6450; fax (425) 917–6590.

SUPPLEMENTARY INFORMATION: The FAA 

has received reports of cracking in the 

fuselage skin and bear strap at the 

forward, upper corner of the L1 entry 

door cutout on Boeing Model 757–200 

series airplanes. A 6.0-inch crack was 

found on an airplane having 27,071 total 

flight cycles. A 1.4-inch crack was also 

found on an airplane having 29,340 total 

flight cycles, and a 1.7-inch crack was 

found in the bear strap on an airplane 

having 26,686 total flight cycles. These 

cracks were found during visual 

inspections during maintenance and 

were attributed to fatigue caused by 

pressurization cycles. 

This condition, if not corrected, could 

result in reduced structural integrity of 

the L1 entry door and consequent rapid 

decompression of the airplane. 

Explanation of Relevant Service 

Information 

The FAA has reviewed and approved 

Boeing Special Attention Service 

Bulletin 757–53–0089, dated March 18, 

2004. The service bulletin describes 

procedures for performing initial and 

repetitive high frequency eddy current 

(HFEC) and low frequency eddy current 

(LFEC) inspections for cracking of the 

fuselage skin around the adjacent 

fasteners, along the edge of the skin and 

bear strap, and the bear strap around the 

fasteners adjacent at the forward, upper 

corner of the L1 entry door cutout; as 

applicable. The service bulletin 

specifies to contact Boeing for repair 

instructions for any cracks found during 

the HFEC and LFEC inspections. 

The service bulletin also describes 

procedures for accomplishing a 

preventative modification, which 

eliminates the need for the repetitive 

inspections. The modification includes 

performing a general visual inspection 

to ensure that the fastener edge margins 

adjacent to the forward, upper corner of 

the L1 entry door cutout are 0.5 inch or 

greater; and related investigative/

corrective actions, if necessary. Related 

investigative actions include repeating 

the general visual inspection at 

specified intervals if the margins are 

less than 0.50 inch or removing the 

fasteners and performing an HFEC 

inspection on the holes in the fuselage 

skin and bear strap if the margins are 

equal to or greater than 0.50 inch. The 

corrective actions include coldworking 

the fastener holes and installing oversized fasteners if no crack is found 

during the HFEC inspection or 

contacting Boeing for repair instructions 

if any crack is found during either the 

general visual or the HFEC inspection. 

Accomplishment of the actions 

specified in the service bulletin is 

intended to adequately address the 

identified unsafe condition. 

Explanation of the Requirements of the 

Rule 

Since an unsafe condition has been 

identified that is likely to exist or 

develop on other airplanes of the same 

type design registered in the United 

States, this AD requires accomplishment 

of the actions specified in the service 

bulletin described previously, except as 

discussed below. This AD also provides 

for optional terminating action for the 

repetitive inspections. 

Differences Between This AD and the 

Service Bulletin 

Although the service bulletin 

specifies that operators contact the 

manufacturer for disposition of certain 

repair conditions, this AD requires 

operators to repair those conditions per 

a method approved by the FAA, or per 

data meeting the type certification basis 

of the airplane approved by a Boeing 

Company Designated Engineering 

Representative who has been authorized 

by the FAA to make such findings. 

Determination of Rule’s Effective Date 

Since a situation exists that requires 

the immediate adoption of this 

regulation, it is found that notice and 

opportunity for prior public comment 

hereon are impracticable, and that good 

cause exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

Although this action is in the form of 

a final rule that involves requirements 

affecting flight safety and, thus, was not 

preceded by notice and an opportunity 

for public comment, comments are 

invited on this rule. Interested persons 

are invited to comment on this rule by 

25482 Federal Register / Vol. 69, No. 89 / Friday, May 7, 2004 / Rules and Regulations 

submitting such written data, views, or 

arguments, as they may desire. 

Communications shall identify the 

Rules Docket number and be submitted 

in triplicate to the address specified 

under the caption ADDRESSES. All 

communications received on or before 

the closing date for comments will be 

considered, and this rule may be 

amended in light of the comments 

received. Factual information that 

supports the commenter’s ideas and 

suggestions is extremely helpful in 

evaluating the effectiveness of the AD 

action and determining whether 

additional rulemaking action would be 

needed. 

Submit comments using the following 

format: 

• Organize comments issue-by-issue. 

For example, discuss a request to 

change the compliance time and a 

request to change the service bulletin 

reference as two separate issues. 

• For each issue, state what specific 

change to the AD is being requested. 

• Include justification (e.g., reasons or 

data) for each request. 

Comments are specifically invited on 

the overall regulatory, economic, 

environmental, and energy aspects of 

the rule that might suggest a need to 

modify the rule. All comments 

submitted will be available, both before 

and after the closing date for comments, 

in the Rules Docket for examination by 

interested persons. A report that 

summarizes each FAA-public contact 

concerned with the substance of this AD 

will be filed in the Rules Docket. 

Commenters wishing the FAA to 

acknowledge receipt of their comments 

submitted in response to this rule must 

submit a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket Number 2004–NM–44–AD.’’ The 

postcard will be date stamped and 

returned to the commenter. 

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. 

The FAA has determined that this 

regulation is an emergency regulation 

that must be issued immediately to 

correct an unsafe condition in aircraft, 

and that it is not a ‘‘significant 

regulatory action’’ under Executive 

Order 12866. It has been determined 

further that this action involves an 

emergency regulation under DOT 

Regulatory Policies and Procedures (44 

FR 11034, February 26, 1979). If it is 

determined that this emergency 

regulation otherwise would be 

significant under DOT Regulatory 

Policies and Procedures, a final 

regulatory evaluation will be prepared 

and placed in the Rules Docket. A copy 

of it, if filed, 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

■ 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

■ 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. Section 39.13 is amended by adding 

the following new airworthiness 

directive:

2004–09–32 Boeing: Amendment 39–13622. 

Docket 2004–NM–44–AD.

Applicability: Model 757–200 series 

airplanes, line numbers 1 through 90 

inclusive; certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously.

To detect and correct cracking of the 

fuselage skin and bear strap at the forward, 

upper corner of the L1 entry door cutout, 

which could result in reduced structural 

integrity of the L1 entry door and consequent 

rapid decompression of the airplane; 

accomplish the following: 

Initial Inspections 

(a) Within 500 flight cycles after the 

effective date of this AD, or within 90 days 

after the effective date of this AD, whichever 

occurs later: Do the inspections of the 

forward, upper corner of the L1 entry door 

cutout specified in paragraphs (a)(1), (a)(2), 

and (a)(3) of this AD, per Part 1 of the Work 

Instructions of Boeing Special Attention 

Service Bulletin 757–53–0089, dated March 

18, 2004. 

(1) Do a high frequency eddy current 

(HFEC) inspection for cracking of the 

fuselage skin around the adjacent fasteners. 

(2) Do an HFEC inspection for cracking 

along the edge of the skin and bear strap. 

(3) Do a low frequency eddy current (LFEC) 

inspection of the bear strap. 

No Crack Detected: Repetitive Inspections 

(b) If no crack is detected during any 

inspection required by paragraph (a) of this 

AD: Repeat the inspections required by 

paragraph (a) of this AD at intervals not to 

exceed 1,400 flight cycles. 

Any Crack Detected: Repair 

(c) If any crack is detected during any 

inspection required by this AD, and the 

service bulletin specifies to contact Boeing 

for appropriate action: Before further flight, 

repair per a method approved by the 

Manager, Seattle Aircraft Certification Office 

(ACO), FAA; or per data meeting the type 

certification basis of the airplane approved 

by a Boeing Company Designated 

Engineering Representative (DER) who has 

been authorized by the Manager, Seattle 

ACO, to make such findings. For a repair 

method to be approved, the approval must 

specifically reference this AD. 

Optional Terminating Modification 

(d) As an alternative to accomplishing the 

inspections required by paragraphs (a) and 

(b) of this AD, do the optional preventative 

modification of the forward, upper corner of 

the L1 entry door cutout, and do all 

applicable related investigative/corrective 

actions by accomplishing all the actions 

specified in Part 2 of the Work Instructions 

of Boeing Special Attention Service Bulletin 

757–53–0089, dated March 18, 2004. 

Accomplishment of the modification 

constitutes terminating action for the 

repetitive inspection requirements of this 

AD. 

Alternative Methods of Compliance 

(e)(1) In accordance with 14 CFR 39.19, the 

Manager, Seattle ACO, FAA, is authorized to 

approve alternative methods of compliance 

(AMOCs) 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 a 

Boeing Company DER who has been 

authorized by the Manager, Seattle ACO, to 

make such findings. 

Incorporation by Reference 

(f) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

Boeing Special Attention Service Bulletin 

757–53–0089, dated March 18, 2004. This 

incorporation by reference was approved by 

the Director of the Federal Register in 

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

part 51. Copies may be obtained from Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. Copies may 

be inspected at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call (202) 741–6030, or go 

to: http://www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html.

Effective Date 

(g) This amendment becomes effective on 

May 24, 2004.

Federal Register / Vol. 69, No. 89 / Friday, May 7, 2004 / Rules and Regulations 25483

Issued in Renton, Washington, on April 28, 

2004. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–10240 Filed 5–6–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2004–NM–70–AD; Amendment 

39–13614; AD 2004–09–24] 

RIN 2120–AA64 

Airworthiness Directives; Gulfstream 

Aerospace LP Model Galaxy and 

Gulfstream 200 Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) that is 

applicable to all Gulfstream Aerospace 

LP Model Galaxy and Gulfstream 200 

airplanes. This action requires repetitive 

inspections of the internal and external 

spring sleeves of the aileron artificial 

feel unit (AFU) for proper lubrication, 

and lubrication if necessary. This action 

is necessary to prevent ice accumulation 

due to water entering the AFU, which 

could restrict or jam the aileron, 

resulting in reduced controllability of 

the airplane. This action is intended to 

address the identified unsafe condition.

DATES: Effective May 24, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of May 24, 

2004. 

Comments for inclusion in the Rules 

Docket must be received on or before 

June 7, 2004.

ADDRESSES: Submit comments in 

triplicate to the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, ANM–114, 

Attention: Rules Docket No. 2004–NM–

70–AD, 1601 Lind Avenue, SW., 

Renton, Washington 98055–4056. 

Comments may be inspected at this 

location between 9 a.m. and 3 p.m., 

Monday through Friday, except Federal 

holidays. Comments may be submitted 

via fax to (425) 227–1232. Comments 

may also be sent via the Internet using 

the following address: 9-anmiarcomment@faa.gov. Comments sent 

via the Internet must contain ‘‘Docket 

No. 2004–NM–70–AD’’ in the subject 

line and need not be submitted in 

triplicate. Comments sent via fax or the 

Internet as attached electronic files must 

be formatted in Microsoft Word 97 or 

2000 or ASCII text. 

The service information referenced in 

this AD may be obtained from 

Gulfstream Aerospace Corporation, P.O. 

Box 2206, Mail Station D25, Savannah, 

Georgia 31402. This information may be 

examined at the FAA, Transport 

Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; or at 

the National Archives and Records 

Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, 

or go to: http://www.archives.gov/

federal_register/

code_of_federal_regulations/

ibr_locations.html.

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2125; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: The Civil 

Aviation Administration of Israel 

(CAAI), which is the airworthiness 

authority for Israel, recently notified the 

FAA that an unsafe condition may exist 

on all Gulfstream Model Galaxy and 

Gulfstream 200 airplanes. The CAAI 

advises that there have been several 

incidents of reduced aileron control due 

to water freezing in the internal and 

external spring sleeves of the aileron 

artificial feel unit (AFU). Investigation 

revealed a lack of the water displacing 

lubricant (Dow Corning 55) that 

prevents water ingress into the sleeves 

of the AFU. Such conditions could 

restrict or jam the aileron, which could 

result in reduced controllability of the 

airplane. 

Explanation of Relevant Service 

Information 

Gulfstream has issued Gulfstream 

Alert Service Bulletin 200–27A–230, 

dated February 18, 2004, which 

describes procedures for repetitive 

inspections of the internal and external 

spring sleeves of the aileron AFU for 

proper lubrication. The service bulletin 

also describes procedures for lubrication 

of the internal and external spring 

sleeves and the face of the nut of the 

AFU with Dow Corning 55 grease, if not 

properly lubricated. 

The service bulletin refers to 

Certification Maintenance Procedure 

(CMP) Code 271051 of Chapter 05–10–

00, of the Gulfstream 200 Airplane 

Maintenance Manual (AMM), as an 

additional source of service information 

for accomplishment of the inspection 

and lubrication of the internal and 

external spring sleeves of the aileron 

AFU. 

Accomplishment of the action 

specified in the service bulletin is 

intended to adequately address the 

identified unsafe condition. The CAAI 

classified this service bulletin as 

mandatory and issued Israeli 

airworthiness directive 27–04–02–06, 

dated February 29, 2004, to ensure the 

continued airworthiness of these 

airplanes in Israel. 

FAA’s Conclusions 

These airplane models are 

manufactured in Israel and are type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Pursuant to this bilateral 

airworthiness agreement, the CAAI has 

kept us informed of the situation 

described above. We have examined the 

findings of the CAAI, reviewed all 

available information, and determined 

that AD action is necessary for products 

of this type design that are certificated 

for operation in the United States. 

Explanation of Requirements of Rule 

Since an unsafe condition has been 

identified that is likely to exist or 

develop on other airplanes of the same 

type design registered in the United 

States, this AD is being issued to 

prevent ice accumulation due to water 

entering the AFU, which could restrict 

or jam the aileron, resulting in reduced 

controllability of the airplane. This AD 

requires repetitive inspections of the 

internal and external spring sleeves of 

the aileron artificial feel unit (AFU) for 

proper lubrication, and lubrication if 

necessary. The actions are required to be 

accomplished in accordance with the 

service bulletin described previously, 

except as discussed below. 

Difference Between Service Bulletin 

and This AD 

Although the service bulletin 

referenced in this AD specifies to 

submit a service reply card to the 

manufacturer, this AD does not include 

such a requirement. 

Clarification of Repetitive Inspection 

Intervals 

Paragraph (a) of this AD requires that 

the initial inspection and lubrication of 

the aileron AFU be repeated at intervals 

not to exceed 300 flight hours. This 

interval is cited in CMP Code 271051 of 

Chapter 05–10–00 of the Gulfstream 200 

AMM, as noted in the Accomplishment