21068 Federal Register / Vol. 61, No. 91 / Thursday, May 9, 1996 / Rules and Regulations

serviceable assembly; and accomplish the

requirements of either paragraph (a)(2)(iii)(A)

or (a)(2)(iii)(C) of this AD at the time

specified in that paragraph.

(A) Option 1. Thereafter, repeat the visual

inspections required by paragraph (a) of this

AD at intervals not to exceed 600 flight

hours; or

(B) Option 2. Install a temporary doubler

on the fuel pipe assembly; and repeat the

visual inspections required by paragraph (a)

of this AD, thereafter, at intervals not to

exceed 15 months. (Replacement of the fuel

pipe assembly with a serviceable pipe

assembly that has been repaired by welding

a doubler in the area of potential damage,

does not require the installation of a

temporary doubler.)

(b) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Los

Angeles Aircraft Certification Office (ACO),

FAA, Transport Airplane Directorate.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Los Angeles ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

(c) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

(d) The actions shall be done in accordance

with McDonnell Douglas Alert Service

Bulletin MD–11–28A083, dated March 13,

1996. 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 McDonnell Douglas Corporation, 3855

Lakewood Boulevard, Long Beach, California

90846, Attention: Technical Publications

Business Administration, Department C1–

L51 (2–60). Copies may be inspected at the

FAA, Transport Airplane Directorate, 1601

Lind Avenue SW., Renton, Washington; or at

the FAA, Los Angeles Aircraft Certification

Office, Transport Airplane Directorate, 3960

Paramount Boulevard, Lakewood, California;

or at the Office of the Federal Register, 800

North Capitol Street NW., suite 700,

Washington, DC.

(e) This amendment becomes effective on

May 24, 1996.

Issued in Renton, Washington, on May 1,

1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–11408 Filed 5–8–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–84–AD; Amendment

39–9611; AD 96–10–06]

RIN: 2120–AA64

Airworthiness Directives; Boeing

Model 737 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 737

series airplanes. This action requires

repetitive inspections to detect cracks of

the lower gate hinge of the forward

galley service door, and replacement of

any cracked hinge. This action also

provides an optional terminating

replacement for the repetitive

inspections. This amendment is

prompted by reports of fatigue cracks

found in the lower gate hinge on the

forward galley service door. The actions

specified in this AD are intended to

prevent such fatigue cracking, which

could lead to the failure of the lower

gate hinge on the forward galley service

door and subsequent loss of cabin

pressure. If the hinge fails, the hinge

and its associated mechanisms and the

emergency escape slide could separate

from the airplane and be ingested into

the engine, or could strike and damage

the flight control surfaces.

DATES: Effective May 24, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 24,

1996.

Comments for inclusion in the Rules

Docket must be received on or before

July 8, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

84–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from Boeing

Commercial Airplane Group, 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 Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Roy

Boffo, Aerospace Engineer, Airframe

Branch, ANM–120S, FAA, Seattle

Aircraft Certification Office, 1601 Lind

Avenue, SW., Renton, Washington;

telephone (206) 227–2780; fax (206)

227–1181.

SUPPLEMENTARY INFORMATION: The FAA

has received several reports of cracks

found in the lower gate hinge on the

forward galley service door on Boeing

Model 737 series airplanes. In two of

these cases, the hinge was severed

completely and the lower gate separated

from the airplane while in flight, which

resulted in loss of cabin pressure. In one

of these cases, the emergency escape

slide was slowly pulled through the gate

opening, and, subsequently, it separated

from the airplane. These airplanes had

accumulated between 13,700 and 66,000

total flight cycles. Investigation revealed

that the cause of such cracking was due

to fatigue. The effects of such fatigue

cracking could lead to the failure of the

lower gate hinge on the forward galley

service door and subsequent loss of

cabin pressure. If the hinge fails, the

hinge and its associated mechanisms

and the emergency escape slide could

separate from the airplane and be

ingested into the engine, or could strike

and damage the flight control surfaces.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Alert Service Bulletin 737–

52A1124, dated January 11, 1996, which

describes procedures for repetitive

detailed visual inspections to detect

cracks of the lower gate hinge of the

forward galley service door, and

replacement of any cracked hinge

found. The service bulletin also

describes procedures for replacement of

the lower gate hinge of the forward

galley service door with an improved

hinge, which will eliminate the need for

the repetitive inspections.

Explanation of the Requirements of the

AD

Since an unsafe condition has been

identified that is likely to exist or

develop on other Boeing Model 737

series airplanes of the same type design,

this AD is being issued to prevent

fatigue cracking and subsequent failure

of the lower gate hinge on the forward

galley service door. This AD requires

repetitive detailed visual inspections to

detect cracks of the lower gate hinge of

the forward galley service door, and

replacement of any cracked hinge

found. This AD also provides for an

optional replacement of the lower gate

hinge of the forward galley service door

with an improved hinge, which

constitutes terminating action for the

repetitive inspection requirements. The

actions are required to be accomplished
Federal Register / Vol. 61, No. 91 / Thursday, May 9, 1996 / Rules and Regulations 21069

in accordance with the alert service

bulletin described previously.

Differences Between the AD and the

Relevant Service Information

Operators should note that, unlike the

various recommended compliance times

specified in the alert service bulletin for

accomplishing the initial inspection of

airplanes (specified as 1,200 flight

cycles after receipt of the service

bulletin for airplanes with 10,000 to

12,000 total flight cycles; 800 flight

cycles after receipt for airplanes with

12,000 to 13,000 total flight cycles; and

400 flight cycles after receipt for

airplanes with 13,000 or more total

flight cycles), this AD requires that all

airplanes be inspected within 400 flight

cycles after the effective date of the AD.

In consideration of not only the

manufacturer’s recommendation, but

the degree of urgency associated with

addressing the subject unsafe condition,

the average utilization of the affected

fleet, and the time necessary to perform

the inspection (3 hours), the FAA has

determined that the various intervals

specified in that alert service bulletin

would not address the identified unsafe

condition in a timely manner. In

addition, the FAA has reviewed the

available data and determined that the

length of cracking is not necessarily

related to the airplane’s flight cycles,

but instead is related to the number of

door cycles. In light of all of these

factors, the FAA finds that a 400-flight

cycle compliance time for initiating the

required actions is warranted, in that it

represents an appropriate interval of

time allowable for affected airplanes to

continue to operate without

compromising safety.

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

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.

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 96–NM–84–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Regulatory Impact

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

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 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

96–10–06 Boeing: Amendment 39–9611.

Docket 96–NM–84–AD.

Applicability: Model 737 series airplanes,

as listed in Boeing Alert Service Bulletin

737–52A1124, dated January 11, 1996; on

which the actions specified in Boeing Service

Bulletin 737–52–1097, Revision 1, dated

April 6, 1989, or Revision 2, dated January

11, 1990, have not been accomplished;

certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise modified, altered, or repaired in

the area subject to the requirements of this

AD. For airplanes that have been modified,

altered, or repaired so that the performance

of the requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (c) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent fatigue cracking of the lower

gate hinge on the forward galley service door,

accomplish the following:

(a) Within 400 flight cycles after the

effective date of this AD, perform a detailed

visual inspection to detect cracks of the

lower gate hinge of the forward galley service

door, in accordance with Boeing Alert

Service Bulletin 737–52A1124, dated January

11, 1996.

(1) If no cracks are detected, repeat the

inspection thereafter at intervals not to

exceed 4,500 flight cycles.

(2) If any crack is detected, prior to further

flight, replace the lower gate hinge with a

new hinge, in accordance with the alert

service bulletin. Accomplishment of the

replacement constitutes terminating action

for this AD.
21070 Federal Register / Vol. 61, No. 91 / Thursday, May 9, 1996 / Rules and Regulations

(b) Replacement of the lower gate hinge of

the forward galley service door with an

improved hinge, in accordance with Boeing

Alert Service Bulletin 737–52A1124, dated

January 11, 1996, constitutes terminating

action for the requirements of this AD.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Seattle

Aircraft Certification Office (ACO), FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Seattle ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(d) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

(e) The inspection and replacement shall

be done in accordance with Boeing Alert

Service Bulletin 737–52A1124, dated January

11, 1996. 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 Airplane Group,

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

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(f) This amendment becomes effective on

May 24, 1996.

Issued in Renton, Washington, on May 1,

1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–11407 Filed 5–8–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–ANE–12; Amendment 39–

9609; AD 96–10–04]

Airworthiness Directives; AlliedSignal,

Inc. LTS101–600 Series Turboshaft

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to AlliedSignal, Inc. LTS101–

600 series turboshaft engines, that

requires installation of an improved

design fuel control. This amendment is

prompted by reports of fuel control

bearings failing prior to the

recommended overhaul period. The

actions specified by this AD are

intended to prevent a fuel control

failure, which could result in an

uncommanded increase or decrease in

engine power.

DATES: Effective June 13, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 13,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from AlliedSignal Engines, 111 South

34th Street, Phoenix, AZ 85072;

telephone (602) 365–2493, fax (602)

365–2210. This information may be

examined at the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, 12 New England Executive

Park, Burlington, MA; or at the Office of

the Federal Register, 800 North Capitol

Street NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Dave Keenan, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (617) 238–7139,

fax (617) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to AlliedSignal, Inc.

Models LTS101–600A–2/A–3 turboshaft

engines was published in the Federal

Register on August 21, 1995 (60 FR

43413). That action proposed to require

the installation of an improved fuel

control in accordance with AlliedSignal

Engines Service Bulletin (SB) No.

LTS101A–73–20–0166, Revision 1,

dated November 21, 1994.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

One commenter, the manufacturer,

states that since the issuance of the

NPRM, AlliedSignal, Inc. has revised

AlliedSignal Engines SB No. LTS101A–

73–20–0166 to recommend the

installation of a screened pneumatic

fitting on the main fuel control (MFC).

The FAA concurs in part. Both revisions

of the SB address the incorporation of

fuel control drive (Meldin) bearings in

the MFC in the same manner, which is

the primary focus of this AD. The FAA

has determined that installation of a

screened pneumatic fitting is not

necessary to prevent a MFC failure due

to lack of bearing lubrication. Therefore,

this final rule references both

AlliedSignal Engines SB No. LTS101A–

73–20–0166, Revision 1, dated

November 21, 1994, and Revision 2,

dated August 1, 1995, but does not

require installation of a screened

pneumatic fitting.

The manufacturer also states that due

to the time required to publish the

NPRM and receive comments, the AD

will not be published prior to

compliance end-date specified in the

NPRM. The FAA concurs and has

extended the compliance end-date in

this final rule to September 1, 1996.

In addition, the FAA is considering

future rulemaking to address other

aircraft installations of the AlliedSignal,

Inc. LT101 series engines.

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

described previously. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

The FAA estimates that 216 engines

installed on aircraft of U.S. registry will

be affected by this AD, that it will take

approximately 2.5 work hours per

engine to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will cost approximately $1,000 per

engine. Based on these figures, the total

cost impact of the AD on U.S. operators

is estimated to be $248,400.

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (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. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.