The U.S. aircraft register, updated daily
FAA orders · airworthiness directive · historical

2013-02-06: Repetitive borescope inspections

FAA order 2013-02-06 is an airworthiness directive in force since February 12, 2013. The FAA's subject line: Repetitive borescope inspections. System: engine.

What it applies to as the FAA lists it

Kind of product
Engine
Makes
Engine Alliance
Models
GP7270, GP7277

Dates and paperwork

In force since
February 12, 2013
Published
January 28, 2013 (signed January 15, 2013)
Docket
FAA-2012-1293
Replaced by
2016-22-11
Status
Historical
The FAA's document
Read the order on the FAA's site

The FAA's summary their words, unchanged

We are adopting a new airworthiness directive (AD) for all Engine Alliance GP7270 and GP7277 turbofan engines. This AD requires initial and repetitive borescope inspections and removal from service before further flight if one or more burn holes are detected, in certain high-pressure turbine (HPT) stage 2 nozzles. This AD also requires mandatory removal from service of these HPT stage 2 nozzles at the next engine shop visit. This AD was prompted by a report received of inadequate cooling of the HPT stage 2 nozzle, leading to damage to the HPT stage 2 nozzle, burn-through of the turbine case, and engine shutdown. We are issuing this AD to prevent HPT stage 2 nozzle failure, leading to uncontrolled fire, engine shutdown, and damage to the airplane.

The order itself the regulatory text, as published

Show the full text (3,167 characters)
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 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2013-02-06 Engine Alliance: Amendment 39-17327; Docket No. FAA-2012- 1293; Directorate Identifier 2012-NE-45-AD. (a) Effective Date This AD is effective February 12, 2013. (b) Affected ADs None. (c) Applicability This AD applies to all Engine Alliance GP7270 and GP7277 turbofan engines with a high-pressure turbine (HPT) stage 2 nozzle, part number (P/N) 2101M24G01, 2101M24G02, or 2101M24G03, installed. (d) Unsafe Condition This AD was prompted by a report received of inadequate cooling of the HPT stage 2 nozzle, leading to damage to the HPT stage 2 nozzle, burn-through of the turbine case, and engine shutdown. Investigation revealed that the event was caused by damage to the HPT stage 2 nozzle due to inadequate part cooling. We are issuing this AD to prevent HPT stage 2 nozzle failure, leading to uncontrolled fire, engine shutdown, and damage to the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (f) Borescope Inspections of the HPT Stage 2 Nozzle (1) Initially borescope inspect (360 degrees) the HPT stage 2 nozzle at the following: (i) Before accumulating 1,500 cycles-since-new (CSN), if the nozzle has fewer than 1,450 CSN on the effective date of this AD. (ii) Within the next 50 cycles, if the nozzle has 1,450 or more CSN on the effective date of this AD. (2) Thereafter, repetitively borescope inspect (360 degrees) the HPT stage 2 nozzle within every 100 additional cycles-in-service. (3) If during any inspection required by this AD, any burn holes are detected through the surface of the nozzle, remove the nozzle from service before further flight. (g) Mandatory Removal From Service of the HPT Stage 2 Nozzles At the next engine shop visit, remove HPT stage 2 nozzles P/N 2101M24G01, 2101M24G02, and 2101M24G03 from service. (h) Definition For the purpose of this AD, an ``engine shop visit'' is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine [[Page 5712]] flanges except that the separation of engine flanges solely for the purposes of transportation without subsequent engine maintenance does not constitute an engine shop visit. (i) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. (j) Related Information For more information about this AD, contactMartin Adler, Aerospace Engineer, Engine & Propeller Directorate, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781-238-7157; fax: 781-238-7199; email: [email protected]. (k) Material Incorporated by Reference None.

Source: FAA Dynamic Regulatory System, airworthiness directives. The FAA's document is the authority; the register counts are this site's, from the FAA register of November 6, 2026. Connections as data: /graph/directive/2013-02-06.json · aircraft systems.