Federal Register / Vol. 62, No. 213 / Tuesday, November 4, 1997 / Rules and Regulations 59565

more than one door between each

section of a crew rest area and the

primary stairway exit. Exit signs

meeting the requirements of

§ 25.812(b)(1)(i) that direct occupants to

the primary stairway exit must be

provided in each section of the crew rest

area.

f. Each smaller area, within the main

crew rest area, created by the

installation of a partition with a door

must individually meet the

requirements of items 4, 5, 6, 7, 9 and

10 of these special conditions with the

door open or closed. The requirements

of items 5 and 9 are not applicable to

lavatories or other small areas that are

not intended to be occupied for

extended periods of time.

Issued in Renton, Washington, on October

23, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service,

ANM–100.

[FR Doc. 97–29125 Filed 11–3–97; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–268–AD; Amendment

39–10190; AD 97–23–02]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 727–100 Series Airplanes

Modified in Accordance With

Supplemental Type Certificate (STC)

SA8472SW

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 727–

100 series airplanes. This action

requires a revision to the Airplane

Flight Manual (AFM) to prohibit

stabilized operation between 60 and 75

percent N1 speed during ground

operations in reverse or forward thrust.

This amendment is prompted by a

report that, during preparation for

takeoff, a transport category airplane

equipped with Rolls-Royce Tay 650–15

engines sustained an engine fan blade

failure, followed by an engine fire. The

actions specified in this AD are

intended to prevent uncontained failure

of engine fan blades due to high cycle

fatigue cracking, which could result in

loss of thrust from the affected engine

and secondary damage to the airplane

and/or fire.

DATES: Effective November 19, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

19, 1997.

Comments for inclusion in the Rules

Docket must be received on or before

January 5, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

268–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The Airplane Flight Manual (AFM)

Supplement referenced in this AD may

be obtained from the Dee Howard

Company, P.O. Box 469001, San

Antonio, Texas 78246. This information

may be examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at

the FAA, Rotorcraft Directorate, 2601

Meacham Boulevard, Fort Worth, Texas;

or at the Office of the Federal Register,

800 North Capitol Street, NW., suite

700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Ron

Filler, Flight Test Pilot, Airplane

Certification Office, ASW–150, FAA,

Rotorcraft Directorate, 2601 Meacham

Boulevard, Fort Worth, Texas, 76137–

4298; telephone (817) 222–5132; fax

(817) 222–5960.

SUPPLEMENTARY INFORMATION: The

Rijksluchtvaartdienst (RLD), which is

the airworthiness authority for the

Netherlands, recently notified the FAA

that it received a report indicating that,

during preparation for takeoff, a Fokker

Model F28 Mark 0100 series airplane

equipped with Rolls-Royce Tay 650–15

engines sustained an engine fan blade

failure, followed by an engine fire.

Investigation revealed that five fan

blades failed at the root area, three fan

blades failed at mid-height, and the

remainder were damaged severely.

Further investigation revealed that all

five fan blades failed due to rapid high

cycle fatigue cracking with low cycle

fatigue cracking origin. Evidence of

rapid high cycle fatigue cracking

indicates that an operational effect is

causing high vibratory stresses. RollsRoyce considers that the high cycle

fatigue cracking was caused by vibration

during previous thrust reverser

applications.

Upon further investigation, the FAA

has determined that Boeing 727QF

airplanes have engine installation and

service records that are similar to

Fokker Model F28 Mark 0100 series

airplanes. Boeing 727QF airplanes are

Boeing Model 727–100 airplanes that

have been modified in accordance with

Supplemental Type Certificate (STC)

SA8472SW, which includes the

installation of Rolls-Royce Tay 651–54

engines.

The FAA has evaluated these findings

and has determined that high-cycle

fatigue cracking of the engine fan blades

could cause uncontained failure of the

engine fan blades. Such fatigue

cracking, if not corrected, could result

in loss of thrust from the affected engine

and secondary damage to the airplane

and/or fire.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Dee Howard Airplane Flight Manual

(AFM) Supplement CR102–F–066,

Change 19, dated October 2, 1997 (for

Boeing 727QF airplanes), which

prohibits stabilized operation between

60 and 75 percent N1 speed during

ground operations in reverse or forward

thrust. Accomplishment of the actions

specified in the service document 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 Boeing Model 727–100

series airplanes of this same type design

registered in the United States, this AD

is issued to require a revision to the

Limitations Section of the FAAapproved AFM to prohibit stabilized

operation between 60 and 75 percent N1

speed during ground operations in

reverse or forward thrust.

These actions are required to be

accomplished in accordance with the

document described previously.

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.
59566 Federal Register / Vol. 62, No. 213 / Tuesday, November 4, 1997 / Rules and Regulations

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 97–NM–268–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 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

97–23–02 Boeing: Amendment 39–10190.

Docket 97–NM–268–AD.

Applicability: Model 727–100 series

airplanes modified in accordance with

Supplemental Type Certificate (STC)

SA8472SW, which includes installation of

Rolls-Royce Tay 651–54 engines; 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 (b) 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 uncontained failure of engine

fan blades due to high cycle fatigue cracking,

which could result in loss of thrust from the

affected engine and secondary damage to the

airplane and/or fire, accomplish the

following:

(a) Within 72 hours after the effective date

of this AD, revise the Limitations Section of

the FAA-approved Airplane Flight Manual

(AFM) by inserting a copy of Dee Howard

Airplane AFM Supplement CR102–F–066,

Change 19, dated October 2, 1997, in the

AFM.

(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, Airplane

Certification Office, ASW–150, FAA,

Rotorcraft Directorate. Operators shall submit

their requests through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Airplane Certification Office,

ASW–150.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Airplane Certification

Office, ASW–150.

(c) Special flight permits may be issued in

accordance with §§ 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 AFM revision shall be done in

accordance with Dee Howard Airplane Flight

Manual Supplement CR102–F–066, Change

19, dated October 2, 1997 (for Boeing 727QF

airplanes), which contains the following list

of effective pages.

Page number

Revision

level shown

on page

Date shown

on page

Title Page ..... 19 ................. November

25, 1992.

1–1, 1–3, 3–

4, 3–15, 4–

61.

Not Shown ... October 2,

1997.

The 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 the Dee Howard Company, P.O. Box

469001, San Antonio, Texas 78246. Copies

may be inspected at the FAA, Transport

Airplane Directorate, 1601 Lind Avenue,

SW., Renton, Washington; or at the FAA,

Rotorcraft Directorate, 2601 Meacham

Boulevard, Fort Worth, Texas; or at the Office

of the Federal Register, 800 North Capitol

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

(e) This amendment becomes effective on

November 19, 1997.

Issued in Renton, Washington, on October

29, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–29114 Filed 11–3–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–225–AD; Amendment

39–10191; AD 97–23–03]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace (Jetstream) Model HS 748

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.