This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

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Rules and Regulations Federal Register

24911

Vol. 63, No. 87

Wednesday, May 6, 1998

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–ANE–09–AD; Amendment

39–10508; AD 98–09–27]

RIN 2120–AA64

Airworthiness Directives; Rolls-Royce,

plc RB211 Trent 768 and 772 Series

Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to Rolls-Royce, plc RB211

Trent 768 and 772 series turbofan

engines. This action requires initial and

repetitive visual inspections of thrust

reverser hinge lugs and attachment ribs

for cracks, and, if necessary, removal

from service and replacement with

serviceable parts. This amendment is

prompted by aircraft certification testing

which revealed that stresses on the

thrust reverser hinge were higher than

had been anticipated during engine

certification. The actions specified in

this AD are intended to prevent thrust

reverser hinge failure, possibly resulting

in liberation of the thrust reverser cowl

duct from the engine nacelle, which

could result in impact damage to other

sections of the aircraft.

DATES: Effective May 21, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 21,

1998.

Comments for inclusion in the Rules

Docket must be received on or before

July 6, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 98–ANE–

09–AD, 12 New England Executive Park,

Burlington, MA 01803–5299. Comments

may also be sent via the Internet using

the following address: ‘‘9-adengineprop@faa.dot.gov’’. Comments

sent via the Internet must contain the

docket number in the subject line.

The service information referenced in

this AD may be obtained from RollsRoyce North America, Inc., 2001 South

Tibbs Ave., Indianapolis, IN 46241;

telephone (317) 230–3995, fax (317)

230–4743. This information may be

examined at the FAA, New England

Region, Office of the Regional 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:

James Lawrence, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (781) 238–7176,

fax (781) 238–7199.

SUPPLEMENTARY INFORMATION: The Civil

Aviation Authority (CAA), which is the

airworthiness authority for the United

Kingdom (UK), recently notified the

FAA that an unsafe condition may exist

on Rolls-Royce, plc (R–R) RB211 Trent

768 and 772 series turbofan engines.

The CAA advises that test

measurements of the pylon to thrust

reverser cowl duct hinge loads revealed

lower than expected hinge lug load

carrying capability. In the event of

failure of one of the thrust reverser cowl

duct hinges, there is a reduced fatigue

life capability on the adjacent hinge.

This could lead to premature failure of

the thrust reverser cowl duct hinges,

resulting in liberation of the cowl duct

from the aircraft. There are currently no

affected engines operated on aircraft of

U.S. registry. This AD, then, is

necessary to require accomplishment of

the required actions for engines

installed on aircraft currently of foreign

registry that may someday be imported

into the U.S. Accordingly, the FAA has

determined that notice and prior

opportunity for comment are

unnecessary and good cause exists for

making this amendment effective in less

than 30 days. This condition, if not

corrected, could result in thrust reverser

hinge failure, possibly resulting in

liberation of the thrust reverser cowl

duct from the engine nacelle, which

could result in impact damage to other

sections of the aircraft.

R–R has issued Service Bulletin (SB)

No. RB.211–78–B115, Revision 1, dated

March 14, 1997, that specifies

procedures for visual inspections of

thrust reverser hinge lugs and

attachment ribs for cracks. The CAA

classified this SB as mandatory and

issued AD 008–03–97 in order to assure

the airworthiness of these engines in the

UK.

This engine model is manufactured in

the UK and is 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 CAA has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the CAA,

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.

Since an unsafe condition has been

identified that is likely to exist or

develop on other engines of the same

type design registered in the United

States, this AD requires initial and

repetitive visual inspections of thrust

reverser hinge lugs and attachment ribs

for cracks, and, if necessary, removal

from service and replacement with

serviceable parts. The actions would be

required to be accomplished in

accordance with the SB described

previously.

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 should identify the

Rules Docket number and be submitted
24912 Federal Register / Vol. 63, No. 87 /Wednesday, May 6, 1998 /Rules and Regulations

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 notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 98–ANE–09–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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 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:

98–09–27 Rolls-Royce, plc: Amendment

39–10508. Docket 98–ANE–09–AD.

Applicability: Rolls-Royce, plc (R–R)

RB211 Trent 768 and 772 series turbofan

engines, installed on but not limited to the

Airbus A330–341 and A330–342 series

aircraft.

Note 1: This airworthiness directive (AD)

applies to each engine identified in the

preceding applicability provision, regardless

of whether it has been modified, altered, or

repaired in the area subject to the

requirements of this AD. For engines 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 thrust reverser hinge failure,

possibly resulting in liberation of the thrust

reverser cowl duct from the engine nacelle,

which could result in impact damage to other

sections of the aircraft, accomplish the

following:

(a) Perform initial and repetitive visual

inspections of thrust reverser hinge lugs and

attachment ribs for cracks, and, if necessary,

remove from service and replace with

serviceable parts, in accordance with R–R

Service Bulletin (SB) No. RB.211–78–B115,

Revision 1, dated March 14, 1997, as follows:

(1) Perform the initial inspection at the

earlier of the following:

(i) 250 hours time in service (TIS) after the

effective date of this AD; or

(ii) 1,200 flight cycles since new (CSN).

(2) Thereafter, perform visual inspections

at intervals not to exceed 1,200 flight cycles

in service (CIS) since last inspection.

(3) If thrust reverser hinge lugs or

attachment ribs are found cracked, remove

from service and replace with serviceable

parts, in accordance with R–R Service

Bulletin (SB) No. RB.211–78–B115, Revision

1, dated March 14, 1997.

(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, Engine

Certification Office. Operators shall submit

their requests through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Engine

Certification Office.

(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 aircraft to

a location where the inspection requirements

of this AD can be accomplished.

(d) The actions required by this AD shall

be performed in accordance with the

following R–R SB:

Document No. Pages Revision Date

RB.211–78–B115 ................................................................................................................................. 1–6 1 March 14, 1997.

Total pages: 6.

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 Rolls-Royce North America, Inc., 2001

South Tibbs Ave., Indianapolis, IN 46241;

telephone (317) 230–3995, fax (317) 230–

4743. Copies may be inspected at the FAA,

New England Region, Office of the Regional

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.

(e) This amendment becomes effective on

May 21, 1998.

Issued in Burlington, Massachusetts, on

April 23, 1998.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 98–11437 Filed 5–5–98; 8:45 am]

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